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  • Other Sources  (313)
  • AIRCRAFT  (313)
  • 2000-2004
  • 1980-1984
  • 1970-1974  (313)
  • 1973  (313)
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  • Other Sources  (313)
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  • 2000-2004
  • 1980-1984
  • 1970-1974  (313)
Year
  • 1
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    Diagnostics of the vibrations of complex rotor systems (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The parameters of the imbalance of a complex rotor system, having n parallel rotors and having six degrees of freedom, can be determined from the parameters of the vibrations of two appropriate degrees of freedom. This considerably simplifies diagnostics of the vibrations of complex rotor systems.
    Keywords: AIRCRAFT
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 100-102
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  • 2
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    Fundamental Consideration of Noise radiation by rotary wings (1973)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: An historical review of progress in understanding of rotor noise is presented. Initial work was principally on propellers, but has many obvious applications to noise from rotary wings. Current understanding of rotor noise radiation is then reviewed in some detail. The principal noise sources appear to be: (1) discrete frequency due to distorted inflow; (2) low frequency broadband due to turbulent inflow, and (3) high frequency broadband due to tip effects. On a helicopter rotor each of these sources seems to be intimately connected with the shed vortex wakes. Tip modifications offer one method for controlling the effects. The implications for the designer are discussed. Rotor subjective noise levels appear to obey a velocity to the eighth power law, independent of thrust. Experiments to rectify some of the present deficiencies in knowledge are suggested.
    Keywords: AIRCRAFT
    Type: AGARD Aerodyn. of Rotary Wings; 18 p
    Format: text
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  • 3
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    A summary of wind tunnel research on tilt-rotors from hover to cruise flight (1973)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: An experimental research program conducted on a series of tilt rotors designed for a range of blades twist is reported. The test facilities used in the program are identified. The objective of the program was to obtain precise results on the influence of blades twist and aeroelasticity on tilt rotor performance from hover to high speed cruise Mach number to 0.7. Five aluminum rigid rotors and one fiber glass composite rotor were tested.
    Keywords: AIRCRAFT
    Type: AGARD Aerodyn. of Rotary Wings; 16 p
    Format: text
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  • 4
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    Recent studies of tire braking performance (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The results from recent studies of some factors affecting tire braking and cornering performance are presented together with a discussion of the possible application of these results to the design of aircraft braking systems. The first part of the paper is concerned with steady-state braking, that is, results from tests conducted at a constant slip ratio or steering angle or both. The second part deals with cyclic braking tests, both single cycle, where brakes are applied at a constant rate until wheel lockup is achieved, and rapid cycling of the brakes under control of a currently operational antiskid system.
    Keywords: AIRCRAFT
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  • 5
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    Role of commercial aircraft in global monitoring systems. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Discussion of the opportunity that the new wide-bodied commercial jet aircraft hold forth as platforms for a global monitoring system that could provide the atmospheric baseline and tropical meteorological data for which there is a pressing need. It is argued that there is no immutable technological impediment to the implementation of such a monitoring program, and that its realization could enhance our knowledge of atmospheric processes at an enormous saving in costs.
    Keywords: AIRCRAFT
    Type: Science; 180; Apr. 27
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  • 6
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    Response of a rigid aircraft to nonstationary atmospheric turbulence. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The plunging response of an aircraft to a type of nonstationary turbulent excitation is considered. The latter consists of stationary Gaussian noise modulated by a well-defined envelope function. The intent of the investigation is to model the excitation experienced by an airplane flying through turbulence of varying intensity and to examine the influence of intensity variations on exceedance frequencies of the gust velocity and the airplane's plunging velocity and acceleration. One analytical advantage of the proposed model is that the Gaussian assumption for the gust excitation is retained. The analysis described herein is developed in terms of an envelope function of arbitrary form; however, numerical calculations are limited to the case of harmonic modulation.
    Keywords: AIRCRAFT
    Type: AIAA Journal; 11; Aug. 197
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  • 7
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    Hypersonic transports - Economics and environmental effects. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: An economic analysis of hypersonic transports is presented to show projected operating costs (direct and indirect) and return on investment. Important assumptions are varied to determine the probable range of values for operating costs and return on investment. The environmental effects of hypersonic transports are discussed and compared to current supersonic transports. Estimates of sideline and flyover noise are made for a typical hypersonic transport, and the sonic boom problem is analyzed and discussed. Since the exhaust products from liquid hydrogen-fueled engines differ from those of kerosene-fueled aircraft, a qualitative assessment of air pollution effects is made.
    Keywords: AIRCRAFT
    Type: Journal of Aircraft; 10; June 197
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  • 8
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    Effect of suspension-line viscous damping on parachute opening load amplification. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A digital computer program was used to investigate the effects of suspension-line viscous damping on the opening loads of a high-altitude parachute system having a specified configuration. It was found (1) that the nonlinear elastic characteristics of the suspension system produce an amplification of the opening load when the viscous damping is negligible, (2) that the load amplification is markedly reduced when the suspension-line viscous damping coefficient is increased, and (3) that the suspension-line viscous damping is an important parameter of opening load amplification for high-velocity parachute inflations.
    Keywords: AIRCRAFT
    Type: Journal of Spacecraft and Rockets; 10; Jan. 197
    Format: text
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  • 9
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    Vortex wake research (1973)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: NASA investigations of aircraft trailing vortices are reviewed. Results obtained in flight on vortex characteristics, such as decay of maximum velocity and vortex drift, are presented for distances behind a generating C-5 aircraft from 0.6 to 13.0 nautical miles. The lateral control activity of a CV-990 aircraft probing the vortices generated by the C-5 aircraft is illustrated and the effect of the C-5 aircraft configuration on this activity is indicated. Results are presented from near-field and far-field studies of accelerated vortex dissipation through the use of various devices such as mass ejection, spoilers, vortex generators, and trailing drag devices.
    Keywords: AIRCRAFT
    Type: AGARD Flight in Turbulence; 14 p
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  • 10
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    A comparison of the overall and broadband noise characteristics of full-scale and model helicopter rotors. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The broadband noise generated by full-scale and model rotors is compared in terms of spectral content and the dependence on tip speed and rotor thrust/pitch angle. Low frequency broadband noise and high frequency broadband noise are studied separately and blade 'scaling' effects are outlined. The degree of agreement between measurements and theoretical and semi-empirical prediction methods is reviewed together with the directionality patterns. The parameters relating to the overall noise are also discussed. It is shown that in general good agreement is obtained between the full-scale and model rotors when considering spectral content and the dependency of the noise levels on tip speed and thrust. The scaling factors usually considered applicable to the low frequency broadband noise do not, however, appear to apply to either the model or full scale rotors.
    Keywords: AIRCRAFT
    Type: Journal of Sound and Vibration; 30; Sept. 22
    Format: text
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  • 11
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    Scaling aircraft noise perception. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Following a brief review of the background to the study, an extensive experiment is described which was undertaken to assess the practical differences between numerous alternative methods for calculating the perceived levels of individual aircraft flyover wounds. One hundred and twenty recorded sounds, including jets, turboprops, piston aircraft and helicopters were rated by a panel of subjects in a pair comparison test. The results were analyzed to evaluate a number of noise rating procedures, in terms of their ability to accurately estimate both relative and absolute perceived noise levels over a wider dynamic range (84-115 dB SPL) than had generally been used in previous experiments. Performances of the different scales were examined in detail for different aircraft categories, and the merits of different band level summation procedures, frequency weighting functions, duration and tone corrections were investigated.
    Keywords: AIRCRAFT
    Type: Journal of Sound and Vibration; 26; Feb. 8
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  • 12
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    Theoretical horizontal tail loads and associated aircraft responses of an autopilot-controlled jet transport flying in turbulence (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: An exploratory analytical study was conducted to analyze problem areas associated with a rigid aircraft controlled by a simple autopilot. The aircraft motion is constrained to the longitudinal phugoid and short period modes. The autopilot characteristics are described. The analytical procedure is explained and stabilizer loads together with some aircraft motions as functions of autopilot gains within the stability boundaries are determined. The effects of center of gravity location and altitude are considered.
    Keywords: AIRCRAFT
    Type: AGARD Flight in Turbulence; 9 p
    Format: text
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  • 13
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    Dynamic loading of aircraft surfaces due to jet exhaust impingement (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: High-lift wing concepts being considered for application to commercial STOL transports are discussed. The flow patterns which produce dynamic loads on these wings are indicated. Measurements of surface pressure and acceleration on a one-half-scale model of an externally blown double-slotted flap are reported. Root-mean-square values, power spectra, and scaling parameters are shown.
    Keywords: AIRCRAFT
    Type: AGARD Symp. on Acoustic Fatigue; 9 p
    Format: text
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  • 14
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    The Buffalo/Spey jet-STOL research aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: The program to design and build a Buffalo/Spey Augmentor-Wing research aircraft is presented. The development of an internally blown flap system for the generation of powered lift is discussed. Modification, development, and testing of the Rolls-Royce Spey engine are reported. The ground tests and first flights of the aircraft are described and the application of the internally blown flap concept for short takeoff military transport aircraft is proposed.
    Keywords: AIRCRAFT
    Type: AGARD Mil. Appl. of V(STOL Aircraft, Vol. 1; 13 p
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  • 15
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    Model studies of crosswind landing-gear configurations for STOL aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A dynamic model was used to directly compare four different crosswind landing gear mechanisms. The model was landed as a free body onto a laterally sloping runway used to simulate a crosswind side force. A radio control system was used for steering to oppose the side force as the model rolled to a stop. The configuration in which the landing gears are alined by the pilot and locked in the direction of motion prior to touchdown gave the smoothest runout behavior with the vehicle maintaining its crab angle throughout the landing roll. Nose wheel steering was confirmed to be better than steering with nose and main gears differentially or together. Testing is continuing to obtain quantitative data to establish an experimental data base for validation of an analytical program that will be capable of predicting full scale results.
    Keywords: AIRCRAFT
    Type: The 8th Aerospace Mech. Symp. te; p 145-154
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  • 16
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    Helicopter visual aid system (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The helicopter visual aid system has been built and flight tested in situations representative of actual flight missions. The mechanisms discussed contributed greatly to the successful performance of the system throughout the 160 hours of flight testing. It has demonstrated that the visual aid concept can provide improved daytime visual capability, greatly improved nighttime capability, surveillance from greater distances and/or altitudes, covert operation at night through the use of the IR searchlight, and a photographic recording at the scene being viewed.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center The 8th Aerospace Mech. Symp.; p 293-309
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  • 17
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    Computer program to perform cost and weight analysis of transport aircraft. Volume 2: Technical volume (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An improved method for estimating aircraft weight and cost using a unique and fundamental approach was developed. The results of this study were integrated into a comprehensive digital computer program, which is intended for use at the preliminary design stage of aircraft development. The program provides a means of computing absolute values for weight and cost, and enables the user to perform trade studies with a sensitivity to detail design and overall structural arrangement. Both batch and interactive graphics modes of program operation are available.
    Keywords: AIRCRAFT
    Type: NASA-CR-132362
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  • 18
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    Concepts for a theoretical and experimental study of lifting rotor random loads and vibrations (further experiments with progressing/regressing rotor flapping modes), Phase 7-C (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experiments with progressing/regressing forced rotor flapping modes have been extended in several directions and the data processing method has been considerably refined. The 16 inch hingeless 2-bladed rotor model was equipped with a new set of high precision blades which removed previously encountered tracking difficulties at high advance ratio, so that tests up to .8 rotor advance ratio could be conducted. In addition to data with 1.20 blade natural flapping frequency data at 1.10 flapping frequency were obtained. Outside the wind tunnel, tests with a ground plate located at different distances below the rotor were conducted while recording the dynamic downflow at a station .2R below the rotor plane with a hot wire anemometer.
    Keywords: AIRCRAFT
    Type: NASA-CR-114711
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  • 19
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    Concepts for a theoretical and experimental study of lifting rotor random loads and vibrations (the effects of some rotor feedback systems on rotor-body dynamics), Phase 7-A (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of three gyroless rotor feedback systems: (1) coning feedback, (2) proportional tilting feedback, and (3) a combination of these on the rotor-body dynamics of hingeless rotorcraft are studied with a simplified analytical model in the advance ratio range from 0 to .8. Combinations of feedback phase angles and control phase angles are selected to minimize control cross coupling and control sensitivity changes between low and high speed flight. For the feedback systems thus selected the effects of feedback gain and control actuator time lag on the stability both with fixed hub and in free flight is studied, whereby the rotorcraft is free in pitch, roll and vertical motion but otherwise restrained. For the free flight is studied, whereby the rotorcraft is free in pitch, roll and vertical motion but otherwise restrained. For the free flight conditions the effects of a horizontal tail are also determined in itself and in combination with the rotor feedback systems.
    Keywords: AIRCRAFT
    Type: NASA-CR-114709
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  • 20
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    Performance of a ballute decelerator towed behind a jet airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An F-104B airplane was modified to investigate the drag and stability characteristics of a ballute decelerator in the wake of an asymmetrical airplane. Decelerator deployments were initiated at a Mach number of 1.3 and an altitude of 15,240 meters (50,000 feet) and terminated when the airplane had decelerated to a Mach number of 0.5. The flight tests indicated that the decelerator had a short inflation time with relatively small opening forces. The drag levels attained with the subject decelerator were less than those obtained with other high-speed decelerators behind a symmetrical tow vehicle. The ballute demonstrated good stability characteristics behind the testbed airplane.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-56019 , H-815
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  • 21
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    Computer program to perform cost and weight analysis of transport aircraft. Volume 1: Summary (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital computer program for evaluating the weight and costs of advanced transport designs was developed. The resultant program, intended for use at the preliminary design level, incorporates both batch mode and interactive graphics run capability. The basis of the weight and cost estimation method developed is a unique way of predicting the physical design of each detail part of a vehicle structure at a time when only configuration concept drawings are available. In addition, the technique relies on methods to predict the precise manufacturing processes and the associated material required to produce each detail part. Weight data are generated in four areas of the program. Overall vehicle system weights are derived on a statistical basis as part of the vehicle sizing process. Theoretical weights, actual weights, and the weight of the raw material to be purchased are derived as part of the structural synthesis and part definition processes based on the computed part geometry.
    Keywords: AIRCRAFT
    Type: NASA-CR-132361
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  • 22
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    V/STOL tilt rotor aircraft study. Volume 10: Performance and stability test of A 1-14.622 Froude scaled Boeing Vertol Model 222 tilt rotor aircraft (Phase 1) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel test data obtained from a 1/4.622 Froude scale Boeing Model 222 with a full span, two prop, tilt rotor, powered model in the Boeing V/STOL wind tunnel are reported. Data were taken in transition and cruise flight conditions and include performance, stability and control and blade loads information. The effects of the rotors, tail surfaces and airframe on the performance and stability are isolated as are the effects of the airframe on the rotors.
    Keywords: AIRCRAFT
    Type: NASA-CR-114603 , D222-10053-1-VOL-10
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  • 23
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    Wind tunnel investigation of a large-scale 25 deg swept-wing jet transport model with an external blowing triple-slotted flap (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted to determine the aerodynamic characteristics of a large-scale subsonic jet transport model with an externally blown triple-slotted flap. The lift of the model was augmented by the turbofan engine exhaust impingement on the flap surface. The model had a 25 deg swept wing of aspect ratio 7.28 and four turbofan engines. The model was tested with two flap extents. One extended from 0.11 to 1.00 of the wing semispan, and the other extended from 0.11 to 0.75 of the wing semispan with a single-slotted aileron from 0.75 to 1.00 of the wing semispan. The results were obtained for several flap deflections with and without the horizontal tail at gross thrust coefficients from 0 to 4.0. Longitudinal and lateral data are presented with three and four engines operating.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62197
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  • 24
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    Automatic control of a helicopter with a hanging load (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An autopilot logic is designed here for controlling a helicopter with a hanging load. A 16th order model for the system is decoupled into four subsystems: (1) a second order system for yawing motion, (2) a second order system for vertical motion, (3) a sixth order system for longitudinal motion, and (4) a sixth order system for lateral motion. A measuring scheme, which could be used in remote areas, is developed and filters are designed to estimate the state variables from these measurements. The autopilot can be used to move the load over short distances without retracting the cables. This is done by automatically shifting the autopilot modes from position-hold (hover) to acceleration-hold to velocity-hold (cruise) to deceleration-hold to velocity-hold (near hover) to position-hold (hover). Use of such an autopilot might save considerable turnaround time. The Sikorsky S-61 helicopter is chosen as an example vehicle. The performance of the controlled system is studied in the presence of longitudinal and lateral winds.
    Keywords: AIRCRAFT
    Type: NASA-CR-136504 , SUDAAR-459
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  • 25
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    Q-FANSTM for general aviation aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Continued growth of general aviation over the next 10 to 15 years is dependent on continuing improvement in aircraft safety, utility, performance and cost. Moreover, these advanced aircraft will need to conform to expected government regulations controlling propulsion system emissions and noise levels. An attractive compact low noise propulsor concept, the Q-FANTM when matched to piston, rotary combustion, or gas turbine engines opens up the exciting prospect of new, cleaner airframe designs for the next generation of general aviation aircraft which will provide these improvements and meet the expected noise and pollution restriction of the 1980 time period. New Q-FAN methodology which was derived to predict Q-FAN noise, weight and cost is presented. Based on this methodology Q-FAN propulsion system performance, weight, noise, and cost trends are discussed. Then the impact of this propulsion system type on the complete aircraft is investigated for several representative aircraft size categories. Finally, example conceptual designs for Q-FAN/engine integration and aircraft installations are presented.
    Keywords: AIRCRAFT
    Type: NASA-CR-114665
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  • 26
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    Takeoff and landing performance and noise measurements of a deflected slipstream STOL airplane with interconnected propellers and rotating cylinder flaps (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A YOV-10A aircraft was modified to incorporate rotating cylinder flaps and interconnected propellers with Lycoming T-53-L11 engines. Flight tests were made to evaluate the low speed handling qualities and performance characteristics. The flight test results indicated that landings could be made with approach speeds of 55 to 65 knots (CL = 4.5) and descent angles of 6 deg to 8 deg for total flap angles of 60 deg to 75 deg. At higher flap angles, deterioration of stability and control characteristics precluded attempts at landing. The noise level on the ground under an 8 deg landing approach path was below 86 PNdB at distances beyond 1 nautical mile from touchdown. Takeoffs were made with 30 deg to 45 deg flaps at lift off speeds of 75 to 80 knots and climb angles of 4 deg to 8 deg. Noise levels were below 83 PNdB at 3.5 nautical miles from the start of ground roll.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62320
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  • 27
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    The effects of an autopilot on airplane responses to turbulence with emphasis on tail loads (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical study has been made to assess the loads developed on the horizontal tail of an autopilot-controlled rigid airplane flying in one-dimensional atmospheric turbulence. The root-mean-square values of rigid-airframe responses and tail-load responses were calculated at five flight conditions, and the behavior of these responses was observed in two autopilot modes: pitch-attitude-hold mode and altitude-control mode. It was found that pitch attitude and altitude can be controlled by the simple autopilot with acceptable or no increases in tail loads.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7231 , L-8756
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  • 28
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    Design and fabrication of an aeroelastic flap element for a Short TakeOff and Landing (STOL) aircraft model (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flap element typifying a third element in the flap system of a short takeoff and landing aircraft was designed, fabricated, and instrumented. It was delivered to NASA for flight-simulated testing. The flap element was aluminum skin-stringer-rib construction with adhesive laminated skins. The tests conducted were as follows: (1) sonic check, (2) thermal expansion, (3) end fitting stiffness, (4) material properties, (5) maximum bending stress in the skin, and (6) effective skin width and stringer spacing.
    Keywords: AIRCRAFT
    Type: NASA-CR-132339 , D6-41253
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  • 29
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    Trends in transport aircraft avionics (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A survey of avionics onboard present commercial transport aircraft was conducted to identify trends in avionics systems characteristics and to determine the impact of technology advances on equipment weight, cost, reliability, and maintainability. Transport aircraft avionics systems are described under the headings of communication, navigation, flight control, and instrumentation. The equipment included in each section is described functionally. However, since more detailed descriptions of the equipment can be found in other sources, the description is limited and emphasis is put on configuration requirements. Since airborne avionics systems must interface with ground facilities, certain ground facilities are described as they relate to the airborne systems, with special emphasis on air traffic control and all-weather landing capability.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62322
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  • 30
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    Low-speed wind tunnel investigation of the lateral-directional characterisitcs of a large-scale variable wing-sweep fighter model in the high-lift configuration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The low-speed characteristics of a large-scale model of the F-14A aircraft were studied in tests conducted in the Ames Research Center 40- by 80-Foot Wind Tunnel. The primary purpose of the present tests was the determination of lateral-directional stability levels and control effectiveness of the aircraft in its high-lift configuration. Tests were conducted at wing angles of attack between minus 2 deg and 30 deg and with sideslip angles between minus 12 deg and 12 deg. Data were taken at a Reynolds number of 8.0 million based on a wing mean aerodynamic chord of 2.24 m (7.36 ft). The model configuration was changed as required to show the effects of direct lift control (spoilers) at yaw, yaw angle with speed brake deflected, and various amounts and combinations of roll control.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62306
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  • 31
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    An exploratory simulation study of a head-up display for general aviation lightplanes (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The concept of a simplified head-up display referred to as a landing-site indicator (LASI) for use in lightplanes is discussed. Results of a fixed-base simulation study exploring the feasibility of the LASI concept are presented in terms of measurements of pilot performance, control-activity parameters, and subjective comments of four test subjects. These subjects, all of whom had various degrees of piloting experience in this type aircraft, performed a series of simulated landings both with and without the LASI starting from different initial conditions in the final approach leg of the landing maneuver.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7456 , L-8897
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  • 32
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    Results of the flight noise measurement program using a standard and modified SH-3A helicopter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A field noise measurement program has been conducted using both a standard SH-3A helicopter and an SH-3A helicopter modified to reduce external noise levels. Modifications included reducing rotor speed, increasing the number of rotor blades, modifying the blade-tip shapes, and acoustically treating the engine air intakes and exhaust. The purpose of this study was to document the noise characteristics recorded on the ground of each helicopter during flyby, hover, landing, and take-off operations. Based on an analysis of the measured results, the average of the overhead, overall, ontrack noise levels was approximately 4 db lower for the modified helicopter than for the standard helicopter. The improved in-flight noise characteristics, and associated small footprint areas and time durations, were judged to be mainly due to tail-rotor noise reductions. The noise reductions were obtained at the expense of required power increases at airspeeds greater than 70 knots for the modified helicopter.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7330 , L-8950
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  • 33
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    Study of quiet turbofan STOL aircraft for short haul transportation (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Conceptual designs of Quiet Turbofan STOL Short-Haul Transport Aircraft for the mid-1980 time period are developed and analyzed to determine their technical, operational, and economic feasibility. A matrix of aircraft using various high-lift systems and design parameters are considered. Variations in aircraft characteristics, airport geometry and location, and operational techniques are analyzed systematically to determine their effects on the market, operating economics, and community acceptance. In these studies, the total systems approach is considered to be critically important in analyzing the potential of STOL aircraft to reduce noise pollution and alleviate the increasing air corridor and airport congestion.
    Keywords: AIRCRAFT
    Type: NASA-CR-2355
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  • 34
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    Wind tunnel investigation of an upper surface blown jet-flap powered-lift configuration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted in the Langley full-scale tunnel to determine the performance and static stability and control characteristics of a four-engine, upper surface blown jet-flap powered-lift configuration with a swept wing. The investigation included test performed over a range of angle of attack (-4 deg to 36 deg), angle of sideslip (-5 deg to 5 deg), and thrust coefficients (0 to 4.32) for both symmetric and engine-out power conditions and for horizontal and vertical tails both on and off. In addition to the four-engine tests, a few tests were made with the outboard engines removed to simulate a twin-engine powered-lift transport configuration.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7399 , L-9051
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  • 35
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    Hypersonic aerodynamic characteristics of an all-body research aircraft configuration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted at Mach 6 to determine the hypersonic aerodynamic characteristics of an all-body, delta-planform, hypersonic research aircraft (HYFAC configuration). The aerodynamic characteristics were obtained at Reynolds numbers based on model length of 2.84 million and 10.5 million and over an angle-of-attack range from minus 4 deg to 20 deg. The experimental results show that the HYFAC configuration is longitudinally stable and can be trimmed over the range of test conditions. The configuration had a small degree of directional stability over the angle-of-attack range and positive effective dihedral at angles of attack greater than 2 deg. Addition of canards caused a decrease in longitudinal stability and an increase in directional stability. Oil-flow studies revealed extensive areas of separated and vortex flow on the fuselage lee surface. A limited comparison of wind-tunnel data with several hypersonic approximations indicated that, except for the directional stability, the tangent-cone method gave adequate agreement at control settings between 5 deg and minus 5 deg and positive lift coefficient. A limited comparison indicated that the HYFAC configuration had greater longitudinal stability than an elliptical-cross-section configuration, but a lower maximum lift-drag ratio.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7358 , L-8971
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  • 36
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    Aerodynamic characteristics of a large-scale model with a swept wing and a jet flap having an expandable duct (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The data from an investigation of the aerodynamic characteristics of the expandable duct-jet flap concept are presented. The investigation was made using a large-scale model in the Ames 40- by 80-foot Wind Tunnel. The expandable duct-jet flap concept uses a lower surface, split flap and an upper surface, Fowler flap to form an internal, variable area cavity for the blowing air. Small amounts of blowing are used on the knee of the upper surface flap and the knee of a short-chord, trailing edge control flap. The bulk of the blowing is at the trailing edge. The flap could extend the full span of the model wing or over the inboard part only, with blown ailerons outboard. Primary configurations tested were two flap angles, typical of takeoff and landing; symmetric control flap deflections, primarily for improved landing performance; and asymmetric aileron and control flap deflections, for lateral control.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62281
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  • 37
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    Study of a control system to alleviate aircraft response to horizontal and vertical gusts (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study is made of the longitudinal response of a STOL airplane equipped with a vanecontrolled gust-alleviation system. Effects of various combinations of design parameters on the responses to horizontal and vertical gusts and to elevator inputs are presented. Almost complete gust alleviation may be obtained with this system when the center of gravity of the STOL airplane is at rearward locations, but pitch stability augmentation is required for satisfactory control characteristics.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7278 , L-8844
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  • 38
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    Acoustic characteristics of a large-scale augmentor wing model at forward speed (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The augmentor wing concept is being studied as one means of attaining short takeoff and landing (STOL) performance in turbofan powered aircraft. Because of the stringent noise requirements for STOL operation, the acoustics of the augmentor wing are undergoing extensive research. The results of a wind tunnel investigation of a large-scale swept augmentor model at forward speed are presented. The augmentor was not acoustically treated, although the compressor supplying the high pressure primary air was treated to allow the measurement of only the augmentor noise. Installing the augmentor flap and shroud on the slot primary nozzle caused the acoustic dependence on jet velocity to change from eighth power to sixth power. Deflecting the augmentor at constant power increased the perceived noise level in the forward quadrant. The effect of airspeed was small. A small aft shift in perceived noise directivity was experienced with no significant change in sound power. Sealing the lower augmentor slot at a flap deflection of 70 deg reduced the perceived noise level in the aft quadrant. The seal prevented noise from propagating through the slot.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-2940 , A-4964
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  • 39
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    Small V/STOL aircraft analysis. Volume 2: Appendices (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A survey of general aviation activities in the United States was principally conducted through interviews with users, manufacturers, trade associations, and government organizations. A list of the organizations interviews is presented. The data became the basis for defining the current and future general aviation missions and performance. The economic characteristics of general aviation are examined. The desires of each organization regarding future aircraft characteristics are summarized.
    Keywords: AIRCRAFT
    Type: NASA-CR-114629 , ATR-73(7302)-1-VOL-2
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  • 40
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    Lightweight, variable solidity knitted parachute fabric (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A parachute fabric for aerodynamic decelerator applications is described. The fabric will permit deployment of the decelerator at high altitudes and low density conditions. The fabric consists of lightweight, highly open, circular knitted parachute fabric with ribbon-like yarns to assist in air deflection.
    Keywords: AIRCRAFT
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  • 41
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    Motorless flight research, 1972 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The proceedings of a symposium on motorless flight research are presented. The subjects discussed are: (1) glider aerodynamic and design, (2) instrumentation, (3) structural concepts and materials, (4) soaring meteorology, (5) self-launching and ultralight sailplanes, and (6) performance testing.
    Keywords: AIRCRAFT
    Type: NASA-CR-2315
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  • 42
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    Remote lift fan study program, volume 4 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study program to select and conduct preliminary design of advanced technology lift fan systems to meet low noise goals of future V/STOL transport aircraft is discussed. This volume contains results of additional studies conducted to support the main preliminary design effort done under the Remote Lift Fan Study Program (Contract NAS3-14406) and a companion effort, the Integral Lift Fan Study (NAS3-14404). These results cover engine emission study, a review of existing engines for research aircraft application and support data for aircraft studies.
    Keywords: AIRCRAFT
    Type: NASA-CR-121277 , GE-R73AEG120-VOL-4
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  • 43
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    Fluidic emergency roll control system (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fluidic emergency roll control system for aircraft stabilization in the event of primary flight control failure was evaluated. The fluidic roll control units were designed to provide roll torque proportional to an electrical command as operated by two diametrically opposed thrust nozzles located in the wing tips. The control package consists of a solid propellant gas generator, two diametrically opposed vortex valve modulated thrust nozzles, and an electromagnetic torque motor. The procedures for the design, development, and performance testing of the system are described.
    Keywords: AIRCRAFT
    Type: NASA-CR-114588
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  • 44
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    Refan program. Phase 1: Summary report (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Refan Program is aimed at a large reduction in aircraft approach and takeoff noise in the vicinity of airports caused by the JT3D-powered 707's and DC-8's and the JT8D-powered 727's, 737's and DC-9's. These aircraft represent a major part of the existing commercial fleet. The noise reductions can be achieved by engine and nacelle modifications in the form of aircraft retrofit kits. Engine turbomachinery noise is reduced by replacing the current two-stage fan with a larger single-stage fan and by nacelle acoustic treatment. Jet noise is reduced by the reduction on jet velocity caused by additional turbine work extraction to drive the larger bypass fan. The predicted net effect of these modifications on installed performance is large noise reductions on both approach and takeoff, increased takeoff thrust, decreased takeoff field length, and maintained or improved aircraft range depending on the amount of acoustic treatment included. The Refan Program is being conducted in two phases under contracts with one engine and two airframe companies. Results of the Phase I work are summarized in this report which describes the refan nacelle configurations studied, the airplane modifications required to install the nacelles, and the resulting airplane performance and noise reductions predicted for all five aircraft.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-71456 , E-7749
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  • 45
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    Full-scale wind-tunnel investigation of effects of slot spoilers on the aerodynamic characteristics of a light twin-engine airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind-tunnel investigation has been conducted to determine the effects of slot spoilers on the longitudinal and lateral aerodynamic characteristics of a full-scale mockup of a light twin-engine airplane. The slots were located along the leading edge of the flaps and were used to modulate the flap-induced lift as a possible means of achieving direct lift control. The data showed that the slots were effective in spoiling up to 61 percent of the flap-induced lift, but that an adverse pitching-moment change (nose up) accompanied opening the slots. Opening the slots was found to decrease slightly the downwash angle at the tail and to increase slightly the longitudinal stability of the model.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7315 , L-8865
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  • 46
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    Results of the noise measurement program on a standard and modified OH-6A helicopter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A field noise measurement program has been conducted on a standard OH-6A helicopter and one that had been modified by reducing the rotor speed, altering rotor tip shape, and treating the engine exhaust and inlet to reduce the external noise levels. The modifications consisted of extensive aircraft design changes resulting in substantial noise reductions following state-of-art noise reduction techniques. The purpose of this study was to document the ground noise characteristics of each helicopter during flyover, hover, landing, and take-off operations. Based on an analysis of the measured results, the average of the overall on-track noise levels of the final modified helicopter was approximately 14 db lower than that for the standard helicopter. Narrow-band-spectra data of the hovering helicopter show a reduction in the overall noise due to the reductions achieved for the lifting main and antitorque tail rotor, engine exhaust, and gear box noise for the modified helicopter. The noise results of the test program are found to correlate generally with noise measurements made previously on this type of aircraft.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7216 , L-8129
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  • 47
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    Experimental and analytical determination of stability parameters for a balloon tethered in a wind (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental and analytical techniques for determining stability parameters for a balloon tethered in a steady wind are described. These techniques are applied to a particular 7.64-meter-long balloon, and the results are presented. The stability parameters of interest appear as coefficients in linearized stability equations and are derived from the various forces and moments acting on the balloon. In several cases the results from the experimental and analytical techniques are compared and suggestions are given as to which techniques are the most practical means of determining values for the stability parameters.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7222 , L-8524
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  • 48
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    V/STOL tilt rotor aircraft study. Volume 5: Definition of stowed rotor research aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a study of folding tilt rotor (stowed rotor) aircraft are presented. The effects of design cruise speed on the gross weight of a conceptual design stowed rotor aircraft are shown and a comparison is made with a conventional (non-folding) tilt rotor aircraft. A flight research stowed rotor design is presented. The program plans, including costs and schedules, are shown for the research aircraft development and a wind tunnel plan is presented for a full scale test of the aircraft.
    Keywords: AIRCRAFT
    Type: NASA-CR-114598 , D222-10060-1-VOL-5
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  • 49
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    V/STOL tilt rotor aircraft study. Volume 6: Preliminary design of a composite wing for tilt rotor research aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a study of the use of composite materials in the wing of a tilt rotor aircraft are presented. An all-metal tilt rotor aircraft was first defined to provide a basis for comparing composite with metal structure. A configuration study was then done in which the wing of the metal aircraft was replaced with composite wings of varying chord and thickness ratio. The results of this study defined the design and performance benefits obtainable with composite materials. Based on these results the aircraft was resized with a composite wing to extend the weight savings to other parts of the aircraft. A wing design was then selected for detailed structural analysis. A development plan including costs and schedules to develop this wing and incorporate it into a proposed flight research tilt rotor vehicle has been devised.
    Keywords: AIRCRAFT
    Type: NASA-CR-114599 , D222-10060-2-VOL-6
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  • 50
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    Effects of flaps on buffet characteristics and wind-rock onset of an F-8C airplane at subsonic and transonic speeds (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind-up-turn maneuvers were performed to establish the values of airplane normal force coefficient for buffet onset, wing-rock onset, and buffet loads with various combinations of leading- and trailing-edge flap deflections. Data were gathered at both subsonic and transonic speeds covering a range from Mach 0.64 to Mach 0.92. Buffet onset and buffet loads were obtained from wingtip acceleration and wing-root bending-moment data, and wing-rock onset was obtained from airplane roll rate data. Buffet onset, wing-rock onset, and buffet loads were similarly affected by the various combinations of leading- and training-edge flaps. Subsonically, the 12 deg leading-edge-flap and trailing-edge-flap combination was most effective in delaying buffet onset, wing-rock onset, and equivalent values of buffet loads to a higher value of airplane normal force coefficient. This was the maximum flap deflection investigated. Transonically, however, the optimum leading-edge flap position was generally less than 12 deg.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-2873 , H-742
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  • 51
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    The results of a low speed wind tunnel test to investigate the effects of installing refan JT8D engines on the McDonnell Douglas DC-9-30 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A low speed wind tunnel test was conducted to assess the effects of the larger JT8D refan nacelles on the stability and control characteristics of the DC-9-30, with emphasis on the deep stall regime. Deep stall pitching moment and elevator hinge moment data, and low angle of attack tail-on and tail-off pitching moment data are presented. The refan nacelle was tested in conjunction with various pylons of reduced span relative to the production DC-9-30 pylon. Also, a horizontal tail that was larger than the production tail was tested. The data show that the refan installation has a small detrimental effect on the DC-9-30 deep stall recovery capability, that recovery characteristics are essentially independent of pylon span, and that the larger horizontal tail significantly increases recovery margins. The deep stall characteristics with the refan installation, within the range of pylon spans tested, are acceptable with no additional design changes anticipated.
    Keywords: AIRCRAFT
    Type: NASA-CR-121220 , MDC-J5961
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  • 52
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    Study of quiet turbofan STOL aircraft for short-haul transportation. Volume 5: Economics (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The economic aspects of the STOL aircraft for short-haul air transportation are discussed. The study emphasized the potential market, the preferred operational concepts, the design characteristics, and the economic viability. Three central issues governing economic viability are as follows: (1) operator economics given the market, (2) the required transportation facilities, and (3) the external economic effects of a set of regional STOL transportation systems.
    Keywords: AIRCRAFT
    Type: NASA-CR-114610 , MDC-J4371-VOL-5
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  • 53
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    Study of quiet turbofan STOL aircraft for short-haul transportation. Volume 6: Systems analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A systems analysis of the quiet turbofan aircraft for short-haul transportation was conducted. The purpose of the study was to integrate the representative data generated by aircraft, market, and economic analyses. Activities of the study were to develop the approach and to refine the methodologies for analytic tradeoff, and sensitivity studies of propulsive lift conceptual aircraft and their performance in simulated regional airlines. The operations of appropriate airlines in each of six geographic regions of the United States were simulated. The offshore domestic regions were evaluated to provide a complete domestic evaluation of the STOL concept applicability.
    Keywords: AIRCRAFT
    Type: NASA-CR-114611 , MDC-J4371-VOL-6
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  • 54
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    Study of quiet turbofan STOL aircraft for short-haul transportation. Volume 4: Markets (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A marketing study to determine the acceptance and utilization of a STOL aircraft short-haul air transportation system was conducted. The relationship between STOL characteristics and the economic and social viability of STOL as a short-haul reliever system was examined. A study flow chart was prepared to show the city pair and traffic split analysis. The national demand for STOL aircraft, as well as the foreign and military markets, were analyzed.
    Keywords: AIRCRAFT
    Type: NASA-CR-114609 , MDC-J4371-VOL-4
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  • 55
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    Study of quiet turbofan STOL aircraft for short-haul transportation. Volume 3: Airports (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The airport siting, design, cost, operation, and implementation aspects of a short takeoff aircraft transportation system are analyzed. Problem areas are identified and alternative solutions or actions required to achieve system implementation by the early 1980's are recommended. Factors associated with the ultimate community acceptance of the STOL program, such as noise, emissions, and congestion, are given special emphasis.
    Keywords: AIRCRAFT
    Type: NASA-CR-114608 , MDC-J4371-VOL-3
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  • 56
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    Study of quiet turbofan STOL aircraft for short-haul transportation. Volume 2: Aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study of the quiet turbofan STOL aircraft for short haul transportation was conducted. The objectives of the study were as follows: (1) to determine the relationships between STOL characteristics and economic and social viability of short haul air transportation, (2) to identify critical technology problems involving introduction of STOL short haul systems, (3) to define representative aircraft configurations, characteristics, and costs, and (4) to identify high payoff technology areas to improve STOL systems. The analyses of the aircraft designs which were generated to fulfill the objectives are summarized. The baseline aircraft characteristics are documented and significant trade studies are presented.
    Keywords: AIRCRAFT
    Type: NASA-CR-114607 , MDC-J4371-VOL-2
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  • 57
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    Leading edge serrations which reduce the noise of low-speed rotors (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Acoustic effects of serrated brass strips attached near the leading edges of two different size rotors were investigated. The two bladed rotors were tested in hover. Rotor rotational speed, blade angle, serration shape, and serration position were varied. The serrations were more effective as noise suppressors at rotor tip speeds less than 135 m/sec (444 ft/sec) than at higher speeds. high frequency noise was reduced but the low frequency rotational noise was little affected. Noise reductions from 4 to 8 db overall sound pressure level and 3 to 17 db in the upper octave bands were achieved on the 1.52 m (5.0 ft) diameter rotor. Noise reductions up to 4 db overall sound pressure level were measured for the 2.59 m (8.5 ft) diameter rotor at some conditions.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7371 , A-4074
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  • 58
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    Noise tests of a model engine-over-the-wing STOL configuration using a multijet nozzle with deflector (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Noise data were obtained with a small scale model stationary STOL configuration that used an eight lobe mixer nozzle with deflector mounted above a 32-cm-chord wing section. The factors varied to determine their effect upon the noise were wing flap angle, nozzle shape, nozzle location, deflector configuration, and jet velocity. The noise from the mixer nozzle model was compared to the noise from a model using a circular nozzle of the same area. The mixer nozzle model was quieter at the low to middle frequencies, while the circular nozzle was quieter at high frequencies. The perceived noise level (PNL) was calculated for an aircraft 10 times larger than the model. The PNL at 500 feet for the mixer nozzle turned out to be within 1 db of the PNL for the circular nozzle. For some configurations at highly directional broadband noise, which could be eliminated by changes in nozzle and/or deflector location, occurred below the wing.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-2871 , E-7459
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  • 59
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    STOL ride control feasibility study (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of developing a ride-smoothing control system for a 20-passenger turboprop STOL transport was assessed. Five different ride-control system configurations with varying degrees of complexity, performance, and cost were investigated. Results indicate that a satisfactory ride-control system can be practically implemented on the aircraft with minimum flight performance degradation.
    Keywords: AIRCRAFT
    Type: NASA-CR-2276 , D3-9052-1
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  • 60
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    A model of wind shear and turbulence in the surface boundary layer (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A model of wind and turbulence has been described for the surface boundary layer. The wind structure in the surface layer is considered to be a function of the surface parameters, stability, and height. The surface parameters considered are: (1) the surface roughness length; (2) the surface friction velocity; and (3) the zero plane displacement height. The stability parameter, Z/L, where L is the Monin-Obukov stability length, describes the thermal effect on the wind profile. The logarithmic wind profile is used to describe the mean wind field in the neutral boundary layer, and a logarithmic profile with a stability defect is used to describe the stable and unstable atmospheric conditions. For the very stable conditions, the logarithmic wind law does not hold. Under this condition, the layers of the atmosphere become disconnected and large scale frontal motions are the predominate factor in defining the wind profile. Figures are presented which represent some typical wind profiles in the very stable condition.
    Keywords: AIRCRAFT
    Type: NASA-CR-2288
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  • 61
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    Studies for determining rapid thrust response requirements and techniques for use in a long range transport aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Propulsion systems proposed for the next generation of long-range transport aircraft will utilize advanced technology to reduce the noise to levels that will be inoffensive to the community. Additional reductions can be realized by adopting steeper glide slopes during the landing approach. The aircraft dynamic characteristics and methods of obtaining rapid engine response during the go-around maneuver from an aborted landing approach are identified and discussed. The study concludes that the present levels of flight safety will not be compromised by the steeper approach.
    Keywords: AIRCRAFT
    Type: NASA-CR-121243 , PWA-4693
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  • 62
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    Point and path performance of light aircraft: A review and analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The literature on methods for predicting the performance of light aircraft is reviewed. The methods discussed in the review extend from the classical instantaneous maximum or minimum technique to techniques for generating mathematically optimum flight paths. Classical point performance techniques are shown to be adequate in many cases but their accuracies are compromised by the need to use simple lift, drag, and thrust relations in order to get closed form solutions. Also the investigation of the effect of changes in weight, altitude, configuration, etc. involves many essentially repetitive calculations. Accordingly, computer programs are provided which can fit arbitrary drag polars and power curves with very high precision and which can then use the resulting fits to compute the performance under the assumption that the aircraft is not accelerating.
    Keywords: AIRCRAFT
    Type: NASA-CR-2272
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  • 63
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    A simulator investigation of the influence of engine response characteristics on the approach and landing for an externally blown flap aircraft. Part 2: Aerodynamic model (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of the influence of engine response characteristics on the approach and landing of an externally blown flap aircraft was conducted using flight simulator facilities. The configuration of the aerodynamic model is described. The aerodynamic characteristics as a function of angle of attack, thrust coefficient, and flap deflection are presented in tabular form and as graphs.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62265(2)
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  • 64
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    A simulator investigation of the influence of engine response characteristics on the approach and landing for an externally blown flap aircraft. Part 1: Description of the simulation and discussion of results (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Investigation of the influence of engine response characteristics on approach and landing operations of a powered lift aircraft were carried out in a piloted ground-based simulator. The aircraft simulated was a four engine, externally-blown jet-flap configuration having an 80 pound wing loading and .56 thrust to weight ratio. Results indicate that for ideal operating conditions and minimal pilot reaction delay, substantial reductions in engine-out wave-off altitude increment and touchdown sink rate for engine-out landings can be achieved with the fast engine compared to the slow engine response. However, delays in pilot reaction of one to two seconds diminish the advantage of rapid thrust response. A need exists for some form of automatic cueing of the pilot or automatic engine control to enable the potential of rapid thrust response to be realized in improving safety in the event of an engine failure.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62265(1)
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  • 65
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    Dual-fuselage aircraft having yawable wing and horizontal stabilizer (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An aircraft configuration consisting of a pair of fuselages parallel to each other and connected by a main wing and a horizontal stabilizer which pivot on the fuselages is described. The pivotal attachment allows the wing to be yawed relative to the fuselages for high speed flight while at the same time spreading the weight and volume distribution of the aircraft along the direction of flight. The main wing is curved upward at the tips to compensate for any roll tendencies caused by its yawed position.
    Keywords: AIRCRAFT
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  • 66
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    Quiet turbofan STOL aircraft for short haul transportation, volume 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see
    Keywords: AIRCRAFT
    Type: NASA-CR-114613
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  • 67
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    Effectiveness evaluation of STOL transport operations (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A short-takeoff and landing (STOL) systems simulation model has been developed and implemented in a computer code (known as STOL OPS) which permits evaluation of the operation of a STOL aircraft and its avionics in a commercial airline operating environment. STOL OPS concentrated on the avionics functions of navigation, guidance, control, communication, hazard aviodance, and systems management. External world factors influencing the operation of the STOL aircraft include each airport and its geometry, air traffic at each airport, air traffic control equipment and procedures, weather (including winds and visibility), and the flight path between each airport served by the route. The development of the STOL OPS program provides NASA a set of computer programs which can be used for detailed analysis of a STOL aircraft and its avionics and permit establishment of system requirements as a function of airline mission performance goals.
    Keywords: AIRCRAFT
    Type: NASA-CR-114631
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  • 68
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    Full scale hover test of a 25 foot tilt rotor (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The tilt rotor underwent a hover performance test on the Aero Propulsion Laboratory whirl stand at Wright-Patterson Air Force Base. The maximum thrust over density ratio measured at the design tip speed of 740 feet per second was 10,016 pounds. This occurred when the power over density ratio was 1721 horsepower. At the hover overspeed rpm, the thrust and power, over density ratio, were 11,008 pounds and 1866 horsepower. During the test, the maximum measured thrust coefficient was 0.177, and the rotor figure of merit exceeded 0.81. Measured lifting efficiency was 8.35 pounds per horsepower at the thrust a 13,000-pound aircraft would require for hover at sea level on a standard day. No effect of compressibility on performance is discernible in the test results (the range of tip Mach numbers tested was 0.55 to 0.71).
    Keywords: AIRCRAFT
    Type: NASA-CR-114626 , REPT-300-099-010
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  • 69
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    Quiet turbofan STOL aircraft for short haul transportation, volume 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The characteristics for a quiet turbofan short takeoff aircraft for short haul transportation applications are discussed. The following subjects are examined: (1) representative aircraft configurations, characteristics, and costs associated with the short haul aircraft development and operation, (2) critical technology and technology related problems to be resolved in successful introduction of representative short haul aircraft, (3) relationships between quiet short takeoff aircraft and the economic and social viability of short haul, and (4) identification of high payoff technology areas. In order to properly evaluate the candidate aircraft designs and to determine their economic viability and community acceptance, a real world scenario was developed and projected to 1990.
    Keywords: AIRCRAFT
    Type: NASA-CR-114612
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  • 70
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    Concepts for a theoretical and experimental study of lifting rotor random loads and vibrations (identification of lifting rotor system parameters from transient response data), Phase 7-B (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: System identification methods have been applied to rotorcraft to estimate stability derivatives from transient flight control response data. While these applications assumed a linear constant coefficient representation of the rotorcraft, the computer experiments used transient responses in flap-bending and torsion of a rotor blade at high advance ratio which is a rapidly time varying periodic system. It was found that a simple system identification method applying a linear sequential estimator also called least square estimator or equation of motion estimator, is suitable for this periodic system and can be used directly if only the acceleration data are noise polluted. In the case of noise being present also in the state variable data the direct application of the estimator gave poor results.
    Keywords: AIRCRAFT
    Type: NASA-CR-114710
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  • 71
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    March 1971 wind tunnel tests of the Dorand DH 2011 jet flap motor, volume 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel tests were conducted of the Dorand DH 2011D jet flap rotor. The data recorded during the tests consist of: (1) multicyclic cam coefficients, (2) stress analysis, (3) vibratory loads, (4) Fourier analysis of flap deflection, and (5) blade bending stress. Data are presented in the form of tables and graphs.
    Keywords: AIRCRAFT
    Type: NASA-CR-114694 , DH-2011-D-E5-VOL-2
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  • 72
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    March 1971 wind tunnel tests of the Dorand DH 2011 jet flap rotor, volume 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of wind tunnel tests, second series of tests performed in the NASA Ames 40 x 80 foot wind tunnel, of the DH 2011 jet-flap rotor are presented and analyzed. The tests have been focused on multicyclic effects and the capability of this rotor to reduce the vibratory loads and stresses in the blades. The reductions of the vibrations and stresses at tip speed ratio of 0.4 have attained 50%. The theory shows further reductions possible, reaching 80%. The results show that the performance characteristics after the modifications introduced since 1965 remained unchanged. The domain of investigation has been enlarged to include the tip speed ratios of 0.6 and 0.7. To analyze the complex aeroelastic phenomena a new analytical technique has been utilized to represent the mathematical model of the rotor. This technique, based on transfer matrices and transfer functions, appears very simple and it is believed that this analysis is applicable to many kinds of investigations involving large numbers of variables.
    Keywords: AIRCRAFT
    Type: NASA-CR-114693 , DH-2011-D-E5-VOL-1
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  • 73
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    Aerodynamic and noise measurements on a quasi-two dimensional augmentor wing model with lobe-type nozzles (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made of the static, wind-on aerodynamic and static noise characteristics of an augmentor wing having lobe type nozzles. The study was made in the Ames 7-by 10-Foot No. 1 Wind Tunnel using a small-scale, quasi-two-dimensional model. Several configurations of lobe nozzles as well as a normal slot nozzle were tested. Results indicate that lobe nozzles offer improved static and wind-on aerodynamics and reduced static noise relative to slot nozzles. Best wind-on performance was obtained when the tertiary gap was closed even though the static thrust augmentation was maximum with the gap open. Static thrust augmentation, wind-on lift and drag, and static noise directivity are presented as well as typical static and wind-on exit velocity profiles, surface pressure distributions and noise spectrums. The data are presented with limited discussion.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62237
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  • 74
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    The Influence of Wing Loading on Turbofan Powered STOL Transports with and Without Externally Blown Flaps (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of wing loading on the design of short takeoff and landing (STOL) transports using (1) mechanical flap systems, and (2) externally blown flap systems are determined. Aircraft incorporating each high-lift method are sized for field lengths of 2,000 feet, 2,500 feet, and 3,500 feet, and for payloads of 40, 150, and 300 passengers, for a total of 18 point-design aircraft. An assumed 1975 level of technology is applied to both concepts in terms of propulsion, weights, active controls, supercritical wing methodology, and acoustics. Low-wing-loading STOL configurations with mechanical flaps are found to be competitive with externally blown flap STOL configurations over wide ranges of payload and field length for the airworthiness rules and technology improvements assumed. Because the results of design studies like this one are sensitive to the ground rules assumed, careful attention is paid to describing the assumptions. These assumptions must be understood before the results are compared with other STOL airplane studies.
    Keywords: AIRCRAFT
    Type: NASA-CR-2320 , D3-8514-7
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  • 75
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    Flight director design for a STOL aircraft. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The study described here was intended to explore some ways of giving the pilot the information necessary to perform as well as an autopilot. A fixed-base flight simulator was built to study pilot/director/aircraft performance. Instrument rated pilots used the different director-displays in an approach down to touchdown, including a flare and decrab maneuver. Two well established areas of control theory are combined in the design of the cockpit display. Optimal control theory and the theory of manual control are used to find the feedback gains required to drive the display symbols. Conclusions based on the simulator are presented. The results show that the director display developed in the work provides more than adequate information for simulated landing in highly turbulent conditions.
    Keywords: AIRCRAFT
    Type: Journal of Aircraft; 10; Aug. 197
    Format: text
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  • 76
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    Review of current sonic boom studies. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Several aspects of the sonic boom phenomena are currently under investigation at The Boeing Co. This work, supported by the NASA and the FAA, includes an in-depth analysis of sonic boom measurements recorded at the BREN tower, a summary and evaluation of sonic boom investigations done in the last decade and a half, and configuration studies to determine practical lower bound sonic boom limits. The BREN tower test program yielded unique and valuable data because it was the first time that vertical profile measurements were made through caustics produced by maneuvers and atmospheric refraction. The objective of the second effort is to compile in a single reference an annotated abstract, including significant results, for each published sonic boom study and to provide a comprehensive review of the current state of the art to aid future researchers. The configuration work is devoted toward determining the feasibility of supersonic transport type airplanes with a primary design goal of acceptable sonic boom characteristics. Each of these investigations is briefly reviewed and significant results are discussed.
    Keywords: AIRCRAFT
    Type: Journal of Aircraft; 10; July 197
    Format: text
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  • 77
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    Experimental landings in a spoiler-equipped light aircraft. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: This report presents the results of a flight test program to determine the effects on landings of wide variations in approach path angle and approach airspeed for different kinds of piloting technique. Over 400 landings were made at approach speeds from 60 to 120 mph and approach path angles from 3 to 18 deg. Several variations of pilot technique involving different operations of the throttle/spoiler control were investigated. It is shown that very large ranges of airspeed and approach path angle can be accommodated with rather moderate penalties in landing distance and difficulty. With the spoiler-equipped aircraft, the best approach speeds are considerably higher than would be usable without spoilers, and approach path angles can be used which are far beyond those normally possible without spoilers.
    Keywords: AIRCRAFT
    Type: Journal of Aircraft; 10; Apr. 197
    Format: text
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  • 78
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    Airport-area airspace used in simulated operations with an experimental powered-lift STOL airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simulation tests were made using an experimental powered-lift STOL airplane to help define airport-area airspace requirements for STOL operations. The operational feasibility and airspace used in take-offs followed by climbing turns, offset (bent localizer) approaches, missed approaches, and two-segment (bent glide-slope) approaches were studied. Flight-director guidance was provided for the approach maneuvers.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7300 , L-8869
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  • 79
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    V/STOL tilt rotor aircraft study. Volume 7: Tilt rotor flight control program feedback studies (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An exploratory study has been made of the use of feedback control in tilt rotor aircraft. This has included the use of swashplate cyclic and collective controls and direct lift control. Various sensor and feedback systems are evaluated in relation to blade loads alleviation, improvement in flying qualities, and modal suppression. Recommendations are made regarding additional analytical and wind tunnel investigations and development of feedback systems in the full scale flight vehicle. Estimated costs and schedules are given.
    Keywords: AIRCRAFT
    Type: NASA-CR-114600 , D222-10060-3-VOL-7
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  • 80
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    Computer simulation of aircraft motions and propulsion system dynamics for the YF-12 aircraft at supersonic cruise conditions (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer simulation of the YF-12 aircraft motions and propulsion system dynamics is presented. The propulsion system was represented in sufficient detail so that interactions between aircraft motions and the propulsion system dynamics could be investigated. Six degree-of-freedom aircraft motions together with the three-axis stability augmentation system were represented. The mixed compression inlets and their controls were represented in the started mode for a range of flow conditions up to the inlet unstart boundary. Effects of inlet moving geometry on aircraft forces and movements as well as effects of aircraft motions on the inlet behavior were simulated. The engines, which are straight subjects, were represented in the afterburning mode, with effects of changes in aircraft flight conditions included. The simulation was capable of operating in real time.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62245 , A-4840
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  • 81
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    Fore and aft elastic response characteristics of size 34x9.9, type 7, 14 ply-rated aircraft tires of bias ply, bias belted, and radial belted design (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted to determine the fore-and-aft elastic response characteristics of aircraft tires of bias ply, bias-belted, and radial-belted design. The investigation consisted of: (1)static and rolling tests, (2)a statistical analysis which related the measured tire elastic characteristics to variations in the vertical load, inflation pressure, braking force and/or tire vertical deflection, and (3) a semi-empirical analysis which related the tire elastic behavior to measured wheel slippage during a steady-state braking. The results of this investigation indicate that the bias-belted tire has the largest spring constant value for most loading conditions and the radial-belted tire has the smallest spring constant value.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-69570
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  • 82
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    The effects on cruise drag of installing refan-engine nacelles on the McDonnell-Douglas DC-9 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A high speed wind tunnel test has been conducted to determine the effect on cruise drag for installing larger JT8D Refan engine nacelles on the Douglas DC-9. Drag data and wing- and nacelle/pylon/fuselage-channel pressure data are presented. Reduced pylon spares, required to minimize effects of the nacelle installation on low-speed deep stall, were investigated. The reduce span pylons resulted in no adverse interference effects. At typical cruise Mach numbers the measured penalty for the Refan installation was less than estimated due to a favorable effect of the larger entering engine stream tube suppressing the wing upper-surface velocities with subsequent wing compressibility drag reduction. Channel pressures show no shock waves or boundary layer separations.
    Keywords: AIRCRAFT
    Type: NASA-CR-121219 , MDC-J5948
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  • 83
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    Life raft stabilizer (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An improved life raft stabilizer for reducing rocking and substantially precluding capsizing is discussed. The stabilizer may be removably attached to the raft and is defined by flexible side walls which extend a considerable depth downwardly to one another in the water. The side walls, in conjunction with the floor of the raft, form a ballast enclosure. A weight is placed in the bottom of the enclosure and water port means are provided in the walls. Placement of the stabilizer in the water allows the weighted bottom to sink, producing submerged deployment thereof and permitting water to enter the enclosure through the port means, thus forming a ballast for the raft.
    Keywords: AIRCRAFT
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  • 84
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    Wind tunnel investigation of static longitudinal and lateral characteristics of a full scale mockup of a light single engine high wing airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The model was a full-scale mockup of a light single-engine high-wing monoplane. Tests were made over an angle-of-attack range of -4 deg to 24 deg and over a sideslip range of plus or minus 8 deg at thrust coefficients of 0, 0.14, and 0.30. Control effectiveness and hinge moments were taken on the aileron, elevator, and rudder for a full range of deflections. Downwash measurements at the tail were obtained for the range of thrust coefficient and flap deflection.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7149 , L-8682
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  • 85
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    Investigation of the Jet Noise Prediction Theory and Application Utilizing the PAO Formulation (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Application of the Phillips theory to engineering calculations of rocket and high speed jet noise radiation is reported. Presented are a detailed derivation of the theory, the composition of the numerical scheme, and discussions of the practical problems arising in the application of the present noise prediction method. The present method still contains some empirical elements, yet it provides a unified approach in the prediction of sound power, spectrum, and directivity.
    Keywords: AIRCRAFT
    Type: NASA-CR-120134
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  • 86
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    Analytical study to define a helicopter stability derivative extraction method, volume 1 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method is developed for extracting six degree-of-freedom stability and control derivatives from helicopter flight data. Different combinations of filtering and derivative estimate are investigated and used with a Bayesian approach for derivative identification. The combination of filtering and estimate found to yield the most accurate time response match to flight test data is determined and applied to CH-53A and CH-54B flight data. The method found to be most accurate consists of (1) filtering flight test data with a digital filter, followed by an extended Kalman filter (2) identifying a derivative estimate with a least square estimator, and (3) obtaining derivatives with the Bayesian derivative extraction method.
    Keywords: AIRCRAFT
    Type: NASA-CR-132371
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  • 87
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    Methods and costs associated with outfitting light aircraft for remote sensing applications (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This document was designed to provide the potential user of a light aircraft remote sensor platform/data gathering system with general information on aircraft definition, implementation complexity, costs, scheduling and operational factors involved in this type of activity. Most of the subject material was developed from actual situations and problem areas encountered during the build-up cycle and early phases of flight operations.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-69938 , ERL-076
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  • 88
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    Design integration and noise studies for jet STOL aircraft. Task 7C: Augmentor wing cruise blowing valveless system. Volume 2: Small-scale development testing of augmentor wing critical ducting components (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Augmentor wing ducting system studies conducted on a valveless system configuration that provides cruise thrust from the augmentor nozzles have shown that most of the duct system pressure loss would occur in the strut-wing duct y-junction and the wing duct-augmentor lobe nozzles. These components were selected for development testing over a range of duct Mach numbers and pressure ratios to provide a technical basis for predicting installed wing thrust loading and for evaluating design wing loading of a particular wing aspect ratios. The flow characteristics of ducting components with relatively high pressure loss coefficients were investigated. The turbulent pressure fluctuations associated with flows at high Mach numbers were analyzed to evaluate potential duct fatigue problems.
    Keywords: AIRCRAFT
    Type: NASA-CR-114623 , D6-40879-VOL-2
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  • 89
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    Design integration and noise studies for jet STOL aircraft. Task 7A: Augmentor wing cruise blowing valveless system. Volume 1: System design and test integration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Exploratory design studies conducted to establish the configuration of an augmentor wing vruise blowing (valveless) system in a 150-passenger STOL airplane were reported in NASA CR-114570. Those studies have been updated to incorporate the results of static rig, flow duct, and wind tunnel tests. Minor adjustments in duct flow velocity, flap length, and blowing nozzle geometry were incorporated to provide airplane characteristics that minimize takeoff gross weight and achieve sideline noise objectives for an advanced commercial STOL airplane.
    Keywords: AIRCRAFT
    Type: NASA-CR-114621 , D6-40950-VOL-1
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  • 90
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    Computer programs for estimating aircraft takeoff and landing performance (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A set of computer programs has been developed to estimate the takeoff and landing maneuver of a given aircraft. The program is applicable to conventional, vectored lift and powered-lift concept aircraft. Portions of the program may also be used to evaluate the static performance of these types of aircraft. The aircraft is treated as a point mass confined to motion in a vertical plane, and rotational dynamics have been neglected. The required input is described and a sample case is presented.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62333
    Format: application/pdf
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  • 91
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    Acoustic characteristics of a large-scale wind tunnel model of an upper-surface blown flap transport having two engines (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The upper-surface blown (USB) flap as a powered-lift concept has evolved because of the potential acoustic shielding provided when turbofan engines are installed on a wing upper surface. The results from a wind tunnel investigation of a large-scale USB model powered by two JT15D-1 turbofan engines are-presented. The effects of coanda flap extent and deflection, forward speed, and exhaust nozzle configuration were investigated. To determine the wing shielding the acoustics of a single engine nacelle removed from the model were also measured. Effective shielding occurred in the aft underwing quadrant. In the forward quadrant the shielding of the high frequency noise was counteracted by an increase in the lower frequency wing-exhaust interaction noise. The fuselage provided shielding of the opposite engine noise such that the difference between single and double engine operation was 1.5 PNdB under the wing. The effects of coanda flap deflection and extent, angle of attack, and forward speed were small. Forward speed reduced the perceived noise level (PNL) by reducing the wing-exhaust interaction noise.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62319
    Format: application/pdf
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  • 92
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    C-5A/orbiter wind tunnel testing and analysis: Piggyback ferry (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel testing and analytical studies of the feasibility of ferrying the NASA Shuttle Orbiter on the C-5A in a piggyback mode have been accomplished. Testing was conducted in the 8x12 foot low speed wind tunnel using an existing 0.0399 scale C-5A model in conjunction with a NASA 0.0405 scale Orbiter model. Six component force and moment data were measured over a range of pitch and yaw angles to determine lift and drag characteristics, lateral/directional stability characteristics and longitudinal and directional control powers. A description of the wind tunnel test program with a run schedule and the complete plotted data for all the test runs are presented. Initial emphasis was given to determining the effects of the Orbiter above the C-5A and the optimum location for minimum interference on C-5A characteristics. A comprehensive series of cruise configurations were tested including a range of Orbiter longitudinal and vertical locations, incidences, and afterbody fairings. Subsequently, a series of configurations were devised during the test program to determine means of recovering directional stability degradation due to Orbiter interference.
    Keywords: AIRCRAFT
    Type: NASA-CR-134184 , LG73ER0193
    Format: application/pdf
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  • 93
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    Design of a flight director/configuration management system for piloted STOL approaches (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design and characteristics of a flight director for V/STOL aircraft are discussed. A configuration management system for piloted STOL approaches is described. The individual components of the overall system designed to reduce pilot workload to an acceptable level during curved, decelerating, and descending STOL approaches are defined. The application of the system to augmentor wing aircraft is analyzed. System performance checks and piloted evaluations were conducted on a flight simulator and the results are summarized.
    Keywords: AIRCRAFT
    Type: NASA-CR-114688 , STI-TR-1015-3
    Format: application/pdf
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  • 94
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    Preliminary investigation of inlet ingestion of a wing tip vortex (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An inlet-coldpipe assembly was placed in a Mach 0.4 stream to ingest the tip vortex of a forward mounted wing. The strongest vortex was produced by a wing angle of attack of 11 degrees. The vortex displayed a tangential velocity of 57 percent of local stream velocity prior to entering the inlet, and a tangential velocity of 25 percent of local velocity at the simulated compressor-face. The total-pressure profiles measured by standard compressor-face rakes were changed by the presence of the vortex only at the highest tested inlet mass-flow ratios.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-68225
    Format: application/pdf
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  • 95
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    High loading, low speed fan study, 5 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A low speed, low noise, single stage fan was designed and tested. Design pressure ratio was 1.5 at a rotor tip speed of 1000 ft/sec. No inlet guide vane was used, the rotor stator was spaced and the number of rotor and stator airfoils was selected for low noise. Tests were conducted with uniform and distorted inlet flows. Stall margin of the initial design was too low for practical application. Airfoil slots and boundary layer and endwall devices did not improve stall margin sufficiently. A redesigned stator with reduced loadings increased stall margin, giving a fan efficiency of 0.883, 15% stall margin, and a 1.474 pressure radio at a specific flow of 41.7 lb/sec sq ft. Casing treatment over rotor tips improved stall margin with distorted inlet flow; vortex generators did not. Blade passing frequency noise increased with rotor relative Mach number. No supersonic fan noise was measured below 105% of design speed. Slotting airfoils, casing treatments, and a reduction of the ratio (number-stators/number-rotors) from (2n + 16) to (2n + 2) had no significant effects on noise.
    Keywords: AIRCRAFT
    Type: NASA-CR-121148 , PWA-4517
    Format: application/pdf
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  • 96
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    Design and development of the spinning mode synthesizer (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design and development of a flexible source of spinning modes which is capable of generating independent spinning waves of controlled complexity and spin speed without the introduction of broad band elements is reported. These features were accomplished through the use of eight commercial loudspeakers located in an equally spaced circular array with diameter of 11 inches and properly phased so that the system could generate a spinning wave. The constructed apparatus was tested in an anechoic environment and found capable of generating a plane, one and two lobed spinning wave of high quality with a sound pressure level of 120 db and at frequencies ranging from 1500 to 2500 Hz at a distance of 4 ft in the far field. The wave speeds investigated varied from 8000 to 18000 rad/sec which represent supersonic peripheral speeds.
    Keywords: AIRCRAFT
    Type: NASA-CR-2260
    Format: application/pdf
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  • 97
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    Experimental investigation of the cornering of a C40 x 14-21 cantilever aircraft tire (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted at the Langley aircraft landing loads and traction facility to define the cornering characteristics of a size C40 x14-21 aircraft tire of cantilever design. These characteristics, which include the cornering-force and drag-force friction coefficients and self-alining torque, were obtained for the tire operating on dry, damp, and flooded runway surfaces over a range of yaw angles from 0 deg to 20 deg and at ground speeds of 5 to 100 knots, both with and without braking. The results of this investigation show that the cornering-force and drag-force friction coefficients and self-alining torque were influenced by the yaw angle, ground speed, brake torque, surface wetness, and the locked-wheel condition.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7203 , L-8766
    Format: application/pdf
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  • 98
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    Structural modeling of aircraft tires (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical and experimental investigation of the feasibility of determining the mechanical properties of aircraft tires from small-scale model tires was accomplished. The theoretical results indicate that the macroscopic static and dynamic mechanical properties of aircraft tires can be accurately determined from the scale model tires although the microscopic and thermal properties of aircraft tires can not. The experimental investigation was conducted on a scale model of a 40 x 12, 14 ply rated, type 7 aircraft tire with a scaling factor of 8.65. The experimental results indicate that the scale model tire exhibited the same static mechanical properties as the prototype tire when compared on a dimensionless basis. The structural modeling concept discussed in this report is believed to be exact for mechanical properties of aircraft tires under static, rolling, and transient conditions.
    Keywords: AIRCRAFT
    Type: NASA-CR-2220 , REPT-05608-16-T-REV
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 99
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    Effect of crossflow velocity on VTOL lift fan blade passing frequency noise generation (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analysis of noise measurements taken during tests of a remote lift fan wing installation, a V/STOL model transport with both lift and lift/cruise fans, and XV5B research aircraft flight tests has indicated a definite increase in pure tone sound pressure level due to crossflow over the face of the life fans. The fan-in-wing and V/STOL model transport tests were conducted in the NASA Ames 40 ft. by 80 ft. wing tunnel and the XV5B flight tests at Moffett Field. Increases up to 10 db were observed for the lift fan installation tested at crossflow to fan tip velocity ratios up to 0.25. Cruise fan noise levels were found to be unaffected by the external flow. The noise level increase was shown to be related to an increase in fan distortion levels.
    Keywords: AIRCRAFT
    Type: NASA-CR-114566
    Format: application/pdf
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  • 100
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    Oblique-wing sonic boom (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted to determine the magnitude of the groundtrack overpressure generated by an oblique-wing transport cruising at Mach 1.4 at 45,000 ft. A conventional swept-wing configuration was included in the study to provide a basis of comparison for the oblique-wing configuration. The results of the investigation have shown that the oblique-wing configuration produces less sonic boom overpressure at cruise lift coefficient than the swept-wing vehicle.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62247
    Format: application/pdf
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