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  • Other Sources  (324)
  • AIRCRAFT  (324)
  • 1980-1984
  • 1970-1974  (324)
  • 1925-1929
  • 1984
  • 1972  (324)
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  • Other Sources  (324)
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  • 1980-1984
  • 1970-1974  (324)
  • 1925-1929
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  • 1
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    Comparison of aerodynamic performance of several STOL concepts (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Wind tunnel tests to determine the aerodynamic characteristics of basically similar short takeoff aircraft were conducted. The investigations were designed to provide data for a systematic direct comparison of five of the concepts considered. The configurations of the five models are illustrated and described. The aerodynamic data are presented in the form of graphs. It was concluded that the most complex systems require the least amount of net thrust.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center STOL Technol.; p 111-120
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  • 2
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    Design integration and noise study for a large STOL augmentor wing transport (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Analysis, design, experimental static testing, wind-tunnel testing, and design integration studies are used to develop an augmentor wing jet flap configuration for a jet STOL transport aircraft having maximum propulsion and aerodynamic performance with minimum noise generation. The program has three basic elements: (1) static testing of a scale wing section to demonstrate augmentor performance and noise characteristics; (2) two-dimensional wind-tunnel testing to determine flight-speed effects on performance, and (3) system design and evaluation that optimizes the complete system and ensures that the design is compatible with the requirements for a large STOL transport having a 500-foot sideline noise of 95 perceived noise decibels (PNdb) or less.
    Keywords: AIRCRAFT
    Type: NASA. Lewis Res. Center Aircraft Engine Noise Reduction; p 291-304
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  • 3
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    Quiet engine demonstration (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A description of the performance test to compare noise output from a quiet engine with acoustic nacelle to the noise output of the JT3D turbofan engine is presented. Tabulations depict comparative thrusts, bypass ratios, core jet velocities, and fan jet velocities for both engines during simulated takeoff and approach performances.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 215-218
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  • 4
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    Fan noise suppression (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The principal suppressor parameters and their relationships have been used to formulate a suppressor design methodology which has been applied to the design of several full-scale suppressors. Tests of these suppressors on several full-scale fans have demonstrated noise reductions of the order of 10 PNdB. The amount of suppression in several instances seems to have been limited by reaching noise floors that are not clearly at the estimated jet noise level but are not far above it. In addition to identifying noise floors, two other areas are considered. The first is attenuation by the fan exhaust suppressors, which seems in most cases to be less than that of the inlet. The second is the effectiveness of outer cowl treatment alone on multiple pure tones. This question relates to whether a high-speed fan can become as quiet as a low-speed fan without a substantial increase in the amount of treatment.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 63-102
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  • 5
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    Flap noise (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Externally-blown-flap noise research can be summarized by the following remarks: With lower-surface blowing, the sources of the flap noise are begining to be understood and the noise scaling laws have been established. Further, progress has been made on suppressing the flap interaction noise at the large flap deflections used during landing. Recent small-scale noise tests of configurations using external upper-surface blowing indicate that engine-over-the-wing configurations may be promising.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 259-290
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  • 6
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    STOL noise sources and fan noise treatment (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: STOL noise goals, noise sources, and their affects on engine and propulsion systems design are considered. It is shown that major noise sources constitute the blown-flap system with its turbofan engine and the augmentor wing propulsion system. Most of the problem areas associated with STOL propulsion systems are defined and the development of a multistage fan engine with proper rotor-stator spacings and low noise core exhaust jet is illustrated. A variable-area acoustic inlet provides near sonic flow conditions during takeoff and landing.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 247-258
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  • 7
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    Quiet engine test results (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The acoustic and aerodynamic test results obtained with the two quiet engines are given in this presentation. Some of the test results reviewed include the performance of the untreated or baseline quiet engines. In addition, test results are shown for various degrees and areas of engine acoustic treatment. Finally, the results obtained on a flight-type, acoustically treated nacelle added to one of the quiet engines is examined.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 183-214
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  • 8
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    Applications to aircraft propulsion systems (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Estimates of the prospects for quiet airplanes in the future are summarized. The SST using afterburning turbojets and no sound suppression is estimated to produce 129 EPNdb on the sideline. Suppression devices and operating techniques can reduce this noise markedly. The present fleet of 707's and DC-8's produces noises nearly as high as 120 decibels on approach. Combinations of sound absorbing devices and engine modifications are expected to give a noise near 100 decibels. The new advanced technology transports (ATT) are being studied with two noise goals in mind: one is 10 decibels and the other is 20 decibels below the FAR level of 106 on takeoff. New trijets using new quiet engines are expected to meet 90 EPNdb. Future advances in technology are expected to yield another 5 decibels to give noise levels of 80 EPNdb. The STOL airplane has a noise goal of 95 EPNdb along a sideline 500 feet from the runway.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 219-246
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  • 9
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    Sonic inlet development for turbofan engines (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The static program has shown to date that very large noise reductions can be achieved by the sonic inlet concept with realistic inlet length and good aerodynamic performance. It is also shown that different inlet concepts produce substantially different results.
    Keywords: AIRCRAFT
    Type: NASA. Lewis Res. Center Aircraft Engine Noise Reduction; p 305-317
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  • 10
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    Quiet engine design highlights (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Three high performance fans were designed, built, and tested, accumulating 444 hours. All three fans are both aerodynamically and mechanically suitable for direct incorporation into engine applications. Two turbofan demonstrators to evaluate both low- and high-speed fan systems were also designed, built, and tested. All components and engine systems are demonstrating high reliability. These components have demonstrated advanced state-of-the-art in acoustics, aerodynamics, and mechanical design.
    Keywords: AIRCRAFT
    Type: NASA. Lewis Res. Center Aircraft Engine Noise Reduction; p 143-162
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  • 11
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    The quiet engine program (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Estimates of noise reductions for high bypass ratio engines show that bypass ratio fan noise increases with increasing bypass ratio and dominates above a bypass ratio of about 1.0. Fan noise reduction to the level of jet noise is achieved by elimination of inlet guide vanes, elimination of second fan stage, and increased spacing between rotor and stator. Quiet engine design studies show that, at bypass ratios near 5 or 6 and with low noise fans, noise reductions in the order of 15 to 20 decibels relative to DC-8 and 707 airplanes engines are possible.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 139-142
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  • 12
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    Fan noise and performance (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Tradeoffs between aerodynamic and acoustic properties of various fan configurations led to the selection of a variety of fans that produce noise levels in the range of 100 to 120 PNdb. Fan configuration and design pressure ratio required for specific mission operations depend in part on the type of mission to be performed. Noise data obtained for single-stage low speed fans, single-stage high speed fans, and two-stage fan engines are presented in table form.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 7-61
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  • 13
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    Quiet engine nacelle design (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Reduction of fan noise emanating from turbofan engines by using acoustically treated nacelles is considered. Test performance prediction for an acoustically lined nacelle having a three ring inlet, a single ring fan duct, and external cowling expect a 15 PNdb fan noise reduction with 5 percent takeoff thrust loss and a 5.4 percent cruise specific fuel consumption increase.
    Keywords: AIRCRAFT
    Type: NASA. Lewis Res. Center Aircraft Engine Noise Reduction; p 163-181
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  • 14
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    Introduction (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Progress reported on principle NASA programs for the reduction of aircraft engine noise emphasizes the Quiet Engine Program. Considered are fan noise and performance, fan noise suppression, and jet noise reduction for a broad spectrum of airplanes including new subsonic airplanes, the older subsonic airplanes in service today, STOL airplanes of the future, and future supersonic transports. Noise reductions achieved in the framework of the Quiet Engine Program are demonstrated and future possible applications of low noise technology to airplanes are discussed.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 1-5
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  • 15
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    Ride evaluation in aerospace and surface vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The vibration environment in a wide range of aerospace and surface vehicles is examined, and definitions related to ride evaluation are reviewed. Three provinces of research and application of ride data are recognized: (1) ride affecting passenger and operator comfort; (2) ride affecting human efficiency; and (3) ride affecting the health and safety of occupants occupationally or repeatedly exposed. Specific reference is made to the proposed ISO guide on human exposure to whole-body vibration. The applications as well as the advantages and limitations of this guide for evaluating vehicle ride are discussed. The derivation of the limits is reviewed with regard to the supporting data and the compromises necessary for wide applicability. Special discussions are included of the frequency and time dependence of these limits and approaches in progress for adjusting them according to different criteria of application.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center Symp. on Vehicle Ride Quality; p 175-196
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  • 16
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    Jet noise (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The main conclusions reached are: (1) At low subsonic jet exhaust velocities, jet noise varies as the velocity to the eighth power; (2) at high subsonic exhaust velocities, jet noise approaches a variation with velocity to the third power; (3) use of the jet density squared overcorrects density effects on jet noise; (4) subsonic and supersonic jet noise levels can be predicted; and (6) use of multielement nozzles and acoustically lined ejectors significantly suppress jet noise at intermediate jet exhaust velocities.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 103-137
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  • 17
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    Exploratory flight investigation of ride quality in simulated STOL environment (1972)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: A flight test experiment is described, in which various aspects of ride qualities were explored. Situations included simulated cruise and terminal area maneuvers, as might be typical of STOL transport operations. Various motion components were studied in isolation and in many combinations. The experiment included runs with and without turbulence, variations in airplane stability and handling qualities, and differences of pilot technique. The ride quality was strongly affected by roll, yaw, and heave motions; but very little by pitching. It was strongly affected by airplane stability and handling qualities and, in some cases, by piloting technique.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center Symp. on Vehicle Ride Quality; p 67-89
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  • 18
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    Ride quality overview (1972)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: An analysis of the factors which affect riding comfort in various modes of transportation is presented. The subjects discussed are: (1) human factor elements in ride quality, (2) current knowledge of flight dynamics and relation to passenger acceptance, (3) study requirements for human factors in ride quality, and (4) possible criteria for human factor in ride quality.
    Keywords: AIRCRAFT
    Type: Symp. on Vehicle Ride Quality; p 1-22
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  • 19
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    Tests and analyses applicable to passenger ride quality of large transport aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: A test program was undertaken to determine airline passenger reaction to vibration environments that might be encountered in a supersonic transport or other large commercial jet aircraft. The principal problem addressed was to determine accelerations of vertical and lateral vibration that people find objectionable. Further questions experimentally posed were: (1) what is the relationship between human reactions to vertical and lateral vibration, (2) to single- and combined-frequency vibration, and (3) to single- and combined-axis vibration? Interest was confined to reactions to vibration in the frequency range of 0.20 to 7.0 Hz, a range typical of the vibration environment of a large airplane. Results indicated an increasing sensitivity to vertical vibration as frequency was increased from 1.0 to 7.0 Hz. Subjects were found most sensitive to lateral vibration in the 1.0 to 3.0 Hz range. There was a nearly linear decrease in sensitivity as frequency of lateral vibration was increased from 3.0 to 7.0 Hz.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center Symp. on Vehicle Ride Quality; p 91-113
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  • 20
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    NASA ride quality program at the Flight Research Center (1972)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: A flight test program to determine the effects of low frequency vibrations on passengers in short haul aircraft is discussed. The objective of the program is to accumulate flight test data on aircraft ride quality in terms of vehicle motion and acceleration and human responses. The subjects discussed are: (1) test procedures, (2) data processing, and (3) the program schedule.
    Keywords: AIRCRAFT
    Type: Symp. on Vehicle Ride Quality; p 247-251
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  • 21
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    An aircraft manufacturer's approach to rideability criteria (1972)
    In:  CASI
    Details
    Publication Date: 2006-04-26
    Description: The approach of an aircraft manufacturer to ride quality in air transportation is presented. The subjects discussed are: (1) the external and internal environment in terms of vibration and acoustic sources and general response, (2) guidelines and criteria reflecting current practice, (3) present and future efforts to develop rideability criteria, and (4) requirements for data, criteria, and research in various rideability areas.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center Symp. on Vehicle Ride Quality; p 23-49
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  • 22
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    Program plan to develop airworthiness standards for STOL aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: A program plan to develop criteria for airworthiness standards for STOL transport aircraft is presented. Initially, three different STOL concepts are to be examined with a goal to arrive at a generalized set of standards. The Breguet 941 deflected-slipstream STOL has been initially evaluated on a piloted motion simulator and in flight. Confidence in establishing criteria for airworthiness standards for STOL transport aircraft has been obtained from these studies.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 345-351
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  • 23
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    Preliminary results of flight tests of the augmentor-wing jet STOL research aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The Augmentor-Wing Jet STOL Research Aircraft has been developed and has started flight tests. The objectives of the program are to compare aerodynamic characteristics predicted from wind-tunnel data with data obtained in flight, to determine flight dynamic characteristics and limitations of the augmentor-wing concepts, and to contribute to the development of STOL design and operational criteria. Initial flight test results have shown that the aerodynamic characteristics are close to values predicted from wind-tunnel tests. The lateral-directional stability and control characteristics are satisfactory for research STOL missions with stability augmentation, but the longitudinal control require improvement. STOL take-off distance over 11 m is about 290 m, and landing approach speeds are between 60 and 65 knots. The investigation of the STOL operational and performance characteristics is continuing.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 259-282
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  • 24
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    Comparisons of simulator and flight results on augmentor-wing jet STOL research aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The considerations involved in making a piloted simulator an effective research tool in the design and development of new aircraft are discussed. An assessment of the limitations of the simulator in depicting real flight as well as the problem of recognizing erroneous results when the simulator is supplied with incorrect input data is made. Examples of the ways in which the simulator is used to design and develop the augmentor-wing aircraft are presented. Four areas of investigation are: (1) to design the lateral control system for proper feel and response, (2) determine the effect of engine failure during approach, (3) develop the best technique for controlling flight path during approach, and (4) the significance of lift loss in ground effect and how to compensate for such loss.
    Keywords: AIRCRAFT
    Type: Stol Technol.; p 283-290
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  • 25
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    Status of STOL ride quality and control (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: A STOL ride-control development program has been initiated with the objective of generating ride-control technology through development and evaluation of an active control system specifically designed to provide ride smoothing on a STOL vehicle. Although much can be learned through analysis, there are deficiencies in technology for translating analysis results into operating hardware. The general approach being followed is to select an existing STOL vehicle for trial and then carry out a study to establish feasibility of a control system or systems to smooth the ride and generate system trade-off data.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 215-226
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  • 26
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    A flight evaluation of curved landing approaches (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The development of STOL technology for application to operational short-haul aircraft is accompanied by the requirement for solving problems in many areas. One of the most obvious problems is STOL aircraft operations in the terminal area. The increased number of terminal operations needed for an economically viable STOL system as compared with the current CTOL system and the incompatibility of STOL and CTOL aircraft speeds are positive indicators of an imminent problem. The high cost of aircraft operations, noise pollution, and poor short-haul service are areas that need improvement. A potential solution to some of the operational problems lies in the capability of making curved landing approaches under both visual and instrument flight conditions.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 245-258
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  • 27
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    Flight-path and airspeed control for the STOL approach and landing (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Analytical investigations and piloted moving base simulator evaluations were conducted for manual control of flight path and airspeed for the approach and landing of a powered lift jet STOL aircraft. Flight-path and airspeed response characteristics were described analytically and were evaluated for the simulation experiments which were carried out on a large motion simulator. The response characteristics were selected and evaluated for a specified path and speed control technique. These characteristics were the initial flight-path response, flight-path overshoot, flight-path-airspeed coupling in response to a change in thrust, and the sensitivity of airspeed to pitch-attitude changes. Results are presented in the form of pilot opinion ratings and commentary, substantiated where appropriate by response time histories and aircraft states at the point of touchdown.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 181-198
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  • 28
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    Study of ground proximity effects on powered-lift STOL landing performance (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Data from wind-tunnel measurements are presented to show the magnitude of adverse ground effects on the longitudinal aerodynamic coefficients of a powered-lift STOL airplane. A steady-state analysis shows the changes in thrust and angle of attack required during the landing approach and flare as the airplane flies close to the ground. The piloting problems that these ground effects may create were investigated with an in-flight simulator to find the consequences of lift loss during the landing-flare maneuver for a STOL transport. Flight tests were made using the variable stability Navion setup with STOL transport aerodynamics and control responses and were flown at design approach speeds and descent conditions.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 199-213
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  • 29
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    Overview of technology sessions (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Short takeoff aircraft technology development related to the requirements for an expanded and improved short-haul air transportation system is discussed. Systems requirements are summarized, principal aircraft requirements are identified, the status of STOL technology is analyzed, and the scope of the technology efforts covered by the conference are outlined. Charts and diagrams are provided to explain system requirements, lift capability trends, and terminal airspace requirements.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 35-42
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  • 30
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    Future short-field aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The application of short takeoff and landing aircraft for improving short-haul air transportation is examined. The contracts with industry to study quiet turbofan short-field aircraft in the short-haul air transportation system are identified. Studies of appropriate propulsion systems are conducted in parallel with the aircraft studies. The objectives of the studies are to: (1) determine economic and social viability of short-haul air transportation, (2) identify critical technology and technology-related problems, (3) define representative aircraft configurations and characteristics to include development and operational costs, and (4) to establish desirable technology advances for improving short-haul transportation systems.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 9-22
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  • 31
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    Short-haul transportation in the 1980's (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The requirements for short-haul air transportation services in the 1980 time period are analyzed. The identification of short takeoff and landing aircraft to perform this service is reviewed. The adequacy of technical programs for developing short-haul aircraft is examined. The characteristics of several candidate short-haul aircraft are described. A system analysis, to include the economic and environmental factors, is developed.
    Keywords: AIRCRAFT
    Type: STOL Technol.; p 1-8
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  • 32
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    S.T.O.L., V.T.O.L., and V./S.T.O.L. - Where do they fit in. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The problems and potential of V/STOL transportation are examined. A detailed review is given of the development, characteristics, and requirements of V/STOL, STOL, and VTOL systems. The problem of whether V/STOL is worth the effort is considered, and it is concluded that such aircraft have a role in meeting real transport requirements, and that their development should be pursued. Finally, a forecast of V/STOL economics is presented, and implementation problems are discussed.
    Keywords: AIRCRAFT
    Type: Technology Review; 74; May 1972
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  • 33
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    The new civil aviation within our grasp. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Noise and congestion present the two main technological constraints on air-transportation growth. Although some of the noise reduction will come with improved flight-path control and steep approaches, the main requirement remains quiet propulsion systems. Higher engine temperatures will compensate for efficiency losses due to noise suppression. Composite structures can reduce structural weight by 20%. New developments in rotorcraft transports are discussed together with advanced subsonic transports of the 1980s and the possibilities for further evolution of the SSTs, leading to a hypersonic aircraft.
    Keywords: AIRCRAFT
    Type: Astronautics and Aeronautics; 10; Jan. 197
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  • 34
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    Analog analysis of a tracked air-cushion vehicle. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The dynamics of tracked air-cushion vehicles considered for high-speed ground transportation systems are examined using a vehicle model represented by a one-degree-of-freedom system. The respective equations of motion are derived, and the control system is discussed. The equations obtained for the cushion are solved using an analog computer. The computer showed the effect of the control technique on the relative motion between vehicle and guideway.
    Keywords: AIRCRAFT
    Type: Instruments and Control Systems; 45; Apr. 197
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  • 35
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    Effects of atmospheric irregularities on sonic-boom propagation. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A review is given of information obtained in recent years concerning the effects on sonic-boom signatures of departures of the atmosphere from a perfectly stratified time invariant model. These effects include the observed random variations in boom overpressures from those expected for a stratified atmosphere, the anomalously large and variable rise times, and the occurrence of spiked or rounded waveforms rather than the characteristic N waves. The extent of the variability in data recorded during actual flight tests is summarized in the form of histograms, representing experimentally obtained probability density functions. The physical mechanisms believed to be responsible for the variations and the anomalous features in the signatures are described. These include refraction and subsequent wavefront rippling by turbulence, the possible focusing or defocusing of rays, the formation of caustics, and the phenomenon of wavefront folding, diffraction, and scattering. Recent statistical theories of shock propagation through a turbulent atmosphere proposed by Crow, George and Plotkin, Pierce, Horning, and others are reviewed.
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  • 36
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    Review of sonic-boom generation theory and prediction methods. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The prediction techniques reviedi he present paper permit the calculation of sonic booms produced by rather complex conventional supersonic aircraft designs performing level nonaccelerated flight in a quiet atmosphere. Basic concepts of supersonic flow analysis, for representation of an airplane as a linear distribution of disturbances and for determination of the resultant pressure field complete with shocks, are outlined. Numerical techniques for implementation of the theory are discussed briefly, and examples of the correlation of theory with experimental data from wind tunnel and flight tests are presented. Special attention is given to presentation of a simplified method for rapid 'first-cut' estimation of farfield bow-shock overpressure. Finally, some problems encountered in attempts at applying the prediction techniques for the nearfield at high supersonic Mach numbers are recognized, and the need for further refinement of present techniques or the development of new systems is discussed.
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  • 37
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    New design goals and a new shape for the SST. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Considerations are given to demonstrate that a wing which pivots as a whole would permit supersonic aircraft which avoid sonic boom and reduce noise around airports. Several such wing designs are discussed. Wind-tunnel tests results are given to support the soundness of this wing design.
    Keywords: AIRCRAFT
    Type: Astronautics and Aeronautics; 10; Dec. 197
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  • 38
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    STOL research at NASA. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of the overall goals, individual objects of ongoing and proposed programs, target dates, and fund requests of NASA's STOL research effort. The realization of a separate STOL short-haul transportation system with a 2000-foot field length capability is shown likely to reduce airport acreage requirements to less than one tenth, approach speed to nearly one half, and airspace required for terminal maneuvering to less than 10% of what conventional high-performance jet aircraft necessitate, and to promise terminal congestion alleviation in areas of high traffic density, improved safety in steep approach, noise abatement, and community annoyance reduction. NASA's described programs will provide the technical foundation upon which industry can base the design and development of aircraft and avionics for the new STOL systems in the latter 1970s, and upon which the government can establish criteria for the certification and regulation of such systems.
    Keywords: AIRCRAFT
    Type: Airport Forum; June 197
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  • 39
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    The transmission of sonic boom signals into rooms through open windows. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: This paper is the second of two companion papers. In the first paper, expressions for the acoustic field generated inside a room with an open window due to incoming transient or periodic signals have been presented. In this paper, the technique has been applied to the specific example of an N-wave type signal. Detailed mathematical analysis is followed by its approximate version and numerical computation. Results of controlled experiments, using simulated sonic booms, have been compared with theoretical predictions.
    Keywords: AIRCRAFT
    Type: Journal of Sound and Vibration; 25; Dec. 22
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  • 40
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    Application of quadratic optimization to supersonic inlet control. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: This paper describes the application of linear stochastic optimal control theory to the design of the control system for the air intake, the inlet, of a supersonic air-breathing propulsion system. The controls must maintain a stable inlet shock position in the presence of random airflow disturbances and prevent inlet unstart. Two different linear time invariant controllers are developed. One is designed to minimize a nonquadratic index, the expected frequency of inlet unstart, and the other is designed to minimize the mean square value of inlet shock motion. The quadratic equivalence principle is used to obtain a linear controller that minimizes the nonquadratic index. The two controllers are compared on the basis of unstart prevention, control effort requirements, and frequency response. It is concluded that while controls designed to minimize unstarts are desirable in that the index minimized is physically meaningful, computation time required is longer than for the minimum mean square shock position approach. The simpler minimum mean square shock position solution produced expected unstart frequency values which were not significantly larger than those of the nonquadratic solution.
    Keywords: AIRCRAFT
    Type: Automatica; 8; Sept
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  • 41
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    Behavior of spherical balloons in wind shear layers. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Analysis of the response of rising spherical balloons to a constant wind shear condition. Wind shear tends to produce a terminal rise rate that is less than the terminal rise rate in the absence of wind shear by no more than 1% of the wind shear and a horizontal balloon velocity defect relative to the local wind with magnitude less than or about equal to 0.2 of the wind shear for most meteorological balloons. An analysis of the behavior of a balloon in a wind field in which the wind shear varies along the vertical is also presented.
    Keywords: AIRCRAFT
    Type: Journal of Geophysical Research; 77; July 20
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  • 42
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    The acoustic response of rooms with open windows to airborne sounds. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The objective of the work described in this and the companion paper was to establish a theory for predicting the sound field generated in a room by a sonic boom incident on an open window. In this paper, some basic theoretical results are presented. First, the case of a normally incident harmonic wave was considered. Expressions for the pressure field were obtained by viewing the room as a terminated duct and by using a Green function method. The concept of mode excitation distribution functions was formulated and used to match the boundary conditions. This concept has been extended for oblique incidence. A modified form of Laplace transform technique was used to obtain expressions in the time domain for transient signals.
    Keywords: AIRCRAFT
    Type: Journal of Sound and Vibration; 25; Dec. 22
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  • 43
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    An assessment of repeated loads on general aviation and transport aircraft. (1972)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An assessment is made of recent repeated loads data from short-haul jet transports and several general aviation airplanes. The jet transport data indicate that except for check flight maneuvers the load histories are essentially independent of operator and airplane type. General aviation data show a large amount of scatter in the repeated load history. The use and geographical location of operations may be the primary means of specifying the repeated loads environment.
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  • 44
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    Flight test experience in aircraft parameter identification (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: An automatic method for determining stability and control derivatives from flight data is presented. The technique, a modification of the Newton-Raphsom method for derivative extraction, has a priori provision that makes use of initial estimates of the derivatives and provides a means of checking the validity of the results. Recommendations for applications of the method are included.
    Keywords: AIRCRAFT
    Type: AGARD Stability and Control te]; 13 p
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  • 45
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    Active control of aeroelastic response (1972)
    In:  CASI
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    Publication Date: 2012-05-23
    Description: Conceptual and wind-tunnel programs leading to the development of technology for applying active controls to the suppression of flutter were studied to provide a powerful tool for required safety margins for flutter in future high-performance supersonic aircraft. The nature of flutter considerations in the design of the U.S. SST prototype aircraft is described as an example of the type of application where active flutter suppression shows promise.
    Keywords: AIRCRAFT
    Type: AGARD Stability and Control te]; 8 p
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  • 46
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    Considerations for stability and control of V/STOL aircraft: A review of AGARD report 577 (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: Revisions which have been made to previous V/STOL handling qualities requirments based on criteria are discussed. A discussion of the pilot's desire for a particular characteristic is given. In addition, data and reference material are provided to back up the proposed criteria to permit the user to understand the limitations of the data on which the criteria are based. A review is included of several controversial areas including pitch control sensitivity, static longitudinal stability, roll control power, roll-yaw cross coupling, and vertical flight path control.
    Keywords: AIRCRAFT
    Type: AGARD Stability and Control te]; 10 p
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  • 47
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    Maneuver and buffet characteristics of fighter aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: The high subsonic and transonic characteristics of fighter aircraft and the factors affecting aerodynamic boundaries, such as maximum obtainable lift, buffet onset, pitchup, wing rock, and nose slice are discussed. Investigations were made using a general research configuration which encompassed a systematic matrix of wing design parameters. These results emphasized the sensitivity to section and planform geometry at the selected design point. The incorporation of variable-wing-geometry devices in the form of leading-edge slats or flaps was shown in a number of flight and wind-tunnel studies to provide controlled flow over a wide range of flight conditions and substantial improvements in maneuver capabilities. Additional studies indicated that the blending of a highly swept maneuver strake with an efficient moderately swept wing offers a promising approach for improving maneuver characteristics at high angles of attack without excessive penalties in structural weight.
    Keywords: AIRCRAFT
    Type: AGARD Fluid Dyn. of Aircraft Stalling; 11 p
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  • 48
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    Revisions to V/STOL handling qualities criteria of AGARD report 408 (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: A brief review of selected handling qualities criteria for V/STOL aircraft shows that although a clearer understanding of the requirements for controversial areas such as roll control power, vertical flight path control, and transition is in hand, considerably more research is needed to refine these criteria for operational IFR activity. Because many items interact to influence the pilots' overall impression of the aircraft's behaviour, additional work of a systematic nature must be done to clarify this aspect. A better definition of a gust model which includes discrete gust effects is needed to firm up criteria for both hover and STOL operation.
    Keywords: AIRCRAFT
    Type: AGARD Handling Qualities Criteria; 8 p
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  • 49
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    Technology for design of transport aircraft. Lecture notes for MIT courses: Seminar 1.61 freshman seminar in air transportation and graduate course 1.201, transportation systems analysis (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design parameters which determine cruise performance for a conventional subsonic jet transport are discussed. It is assumed that the aircraft burns climb fuel to reach cruising altitude and that aeronautical technology determines the ability to carry a given payload at cruising altitude. It is shown that different sizes of transport aircraft are needed to provide the cost optimal vehicle for different given payload-range objectives.
    Keywords: AIRCRAFT
    Type: Proc. of the NASA(MIT Workshop on Airline Systems Analysis, Vol. 1; 50 p
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  • 50
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    Apollo 15 main-parachute failure (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In the investigation of the failure of one of the three main parachutes of the Apollo 15 spacecraft, which collapsed at approximately 1825 meters after operating properly from deployment at 3050 meters, three conditions considered to be possible causes of the failure were produced. The suspect conditions were the proximity of the forward heat shield that passed the spacecraft at approximately 1825 meters, the dumping of the reaction control system hypergolic propellants at approximately 1825 meters, and the failing of a riser link found on a recovered parachute. (The failed parachute was not recovered). The remaining two parachutes functioned as planned and averted a catastrophic failure. The conclusions concerning the cause of the failure are discussed.
    Keywords: AIRCRAFT
    Type: The 7th Aerospace Mech. Symp.; p 137-148
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  • 51
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    Statistical analysis of mission profile parameters of civil transport airplanes (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The statistical analysis of flight times as well as airplane gross weights and fuel weights of jet-powered civil transport airplanes has shown that the distributions of their frequency of occurrence per flight can be presented approximately in general form. Before, however, these results may be used during the project stage of an airplane for defining a typical mission profile (the parameters of which are assumed to occur, for example, with a probability of 50 percent), the following points have to be taken into account. Because the individual airplanes were rotated during service, the scatter between the distributions of mission profile parameters for airplanes of the same type, which were flown with similar payload, has proven to be very small. Significant deviations from the generalized distributions may occur if an operator uses one airplane preferably on one or two specific routes. Another reason for larger deviations could be that the maintenance services of the operators of the observed airplanes are not representative of other airlines. Although there are indications that this is unlikely, similar information should be obtained from other operators. Such information would improve the reliability of the data.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation; p 541-563
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  • 52
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    Fatigue failure of metal components as a factor in civil aircraft accidents (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A review of records maintained by the National Transportation Safety Board showed that 16,054 civil aviation accidents occurred in the United States during the 3-year period ending December 31, 1969. Material failure was an important factor in the cause of 942 of these accidents. Fatigue was identified as the mode of the material failures associated with the cause of 155 accidents and in many other accidents the records indicated that fatigue failures might have been involved. There were 27 fatal accidents and 157 fatalities in accidents in which fatigue failures of metal components were definitely identified. Fatigue failures associated with accidents occurred most frequently in landing-gear components, followed in order by powerplant, propeller, and structural components in fixed-wing aircraft and tail-rotor and main-rotor components in rotorcraft. In a study of 230 laboratory reports on failed components associated with the cause of accidents, fatigue was identified as the mode of failure in more than 60 percent of the failed components. The most frequently identified cause of fatigue, as well as most other types of material failures, was improper maintenance (including inadequate inspection). Fabrication defects, design deficiencies, defective material, and abnormal service damage also caused many fatigue failures. Four case histories of major accidents are included in the paper as illustrations of some of the factors invovled in fatigue failures of aircraft components.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center Advanced Approaches to Fatigue Evaluation; p 611-630
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  • 53
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    Fastening on the F-14A for cost effective fatigue resistance (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Cost effectiveness airframe considerations dictated a variable geometry wing design that requires weight optimization, maximum working stress resistance and minimum fatigue concentration factors. The extensive use of titanium structural materials employed electron beam welding methods and interference fit fastening techniques as principle mechanical joining means for economic F-14A production and reliability engineering.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center Proc. of the Symp. on Welding, Bonding, and Fastening; 20 p
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  • 54
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    Titanium honeycomb structure (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A brazed titanium honeycomb sandwich system for supersonic transport wing cover panels provides the most efficient structure spanwise, chordwise, and loadwise. Flutter testing shows that high wing stiffness is most efficient in a sandwich structure. This structure also provides good thermal insulation if liquid fuel is carried in direct contact with the wing structure in integral fuel tanks.
    Keywords: AIRCRAFT
    Type: NASA. Langley Res. Center Proc. of the Symp. on Welding, Bonding, and Fastening; 21 p
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  • 55
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    Ride Quality Criteria for Large Commercial Helicopters (1972)
    In:  CASI
    Details
    Publication Date: 2018-10-19
    Description: A review of major ride-quality criteria used in the design of commercial helicopters, some of the limitations of these criteria, research programs conducted to better define these criteria, and some recommended research programs is presented. Primary emphasis is given to the question of noise and vibration criteria for passenger acceptance and comfort.
    Keywords: AIRCRAFT
    Type: NASA. Langley Research Center Symposium on Vehicle Ride Quality; 51-66
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  • 56
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    The development of an augmentor wing jet STOL research airplane (modified C-8A). Volume 1: Summary (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A project to develop an experimental aircraft for use as an inflight demonstrator of the augmentor wing, short takeoff concept is discussed. The required modifications were made on a de Havilland C-8A aircraft. The modifications to the aircraft are explained and the performance of the modified aircraft is reported.
    Keywords: AIRCRAFT
    Type: NASA-CR-114503 , D6-40720-1-VOL-1
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  • 57
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    Design integration and noise studies for jet STOL aircraft. Task 7A: Augmentor wing cruise blowing valveless system. Volume 2: Design exploration (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A design integration study program was conducted to determine size and performance parameters of an augmentor wing cruise blowing (valveless) system in a 150-passenger STOL airplane for the purpose of defining size and configuration of static rig, flow duct, and wind tunnel test hardware. The studies encompassed blowing systems powered by low-pressure (single stage) and high-pressure (three and four stage) engine fans. A range of wing aspect ratios, wing thicknesses, and duct flow velocity effects were investigated to establish airplane characteristics which minimize takeoff gross weight while achieving sideline noise requirements for an advanced commercial STOL airplane.
    Keywords: AIRCRAFT
    Type: NASA-CR-114570 , D6-40829-VOL-2
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  • 58
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    A summary of wind tunnel research on tilt-rotors from hover to cruise flight. (1972)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Keywords: AIRCRAFT
    Type: ONERA, TP NO. 1133
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  • 59
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    The development of an augmentor wing jet STOL research aircraft (modified C-8A). Volume 2: Analysis of contractor's flight test (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The initial flight test phase of the modified C-8A airplane was conducted. The primary objective of the testing was to establish the basic airworthiness of the research vehicle. This included verification of the structural design and evaluation of the aircraft's systems. Only a minimum amount of performance testing was scheduled; this has been used to provide a preliminary indication of the airplane's performance and flight characteristics for future flight planning. The testing included flutter and loads investigations up to the maximum design speed. The operational characteristics of all systems were assessed including hydraulics, environmental control system, air ducts, the vectoring conical nozzles, and the stability augmentation system (SAS). Approaches to stall were made at three primary flap settings: up, 30 deg and 65 deg, but full stalls were not scheduled. Minimum control speeds and maneuver margins were checked. All takeoffs and landings were conventional, and STOL performance was not scheduled during this phase of the evaluation.
    Keywords: AIRCRAFT
    Type: NASA-CR-114504 , D6-40720-2-VOL-2
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  • 60
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    Automated design optimization of supersonic airplane wing structures under dynamic constraints (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The problems of the preliminary and first level detail design of supersonic aircraft wings are stated as mathematical programs and solved using automated optimum design techniques. The problem is approached in two phases: the first is a simplified equivalent plate model in which the envelope, planform and structural parameters are varied to produce a design, the second is a finite element model with fixed configuration in which the material distribution is varied. Constraints include flutter, aeroelastically computed stresses and deflections, natural frequency and a variety of geometric limitations.
    Keywords: AIRCRAFT
    Type: NASA-CR-112319
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  • 61
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    Feasibility study of applying an advanced composite structure technique to the fabrication of helicopter rotor blades (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The fabrication of helicopter rotary wings from composite materials is discussed. Two composite spar specimens consisting of compressively prestressed stainless steel liner over-wrapped with pretensioned fiberglass were constructed. High liner strength and toughness together with the prescribed prestresses and final sizing of the part are achieved by means of cryogenic stretch forming of the fiber wrapped composite spar at minus 320 F, followed by release of the forming pressure and warm up to room temperature. The prestresses are chosen to provide residual compression in the metal liner under operating loads.
    Keywords: AIRCRAFT
    Type: NASA-CR-112191 , ARDE-J/N-41003
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  • 62
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    Lateral-directional aerodynamic characteristics of light, twin-engine, propeller driven airplanes (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical procedures and design data for predicting the lateral-directional static and dynamic stability and control characteristics of light, twin engine, propeller driven airplanes for propeller-off and power-on conditions are reported. Although the consideration of power effects is limited to twin engine airplanes, the propeller-off considerations are applicable to single engine airplanes as well. The procedures are applied to a twin engine, propeller driven, semi-low-wing airplane in the clean configuration through the linear lift range. The calculated derivative characteristics are compared with wind tunnel and flight data. Included in the calculated characteristics are the spiral mode, roll mode, and Dutch roll mode over the speed range of the airplane.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6946 , H-694
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  • 63
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    Study of low density air transportation concepts (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Low density air transport refers to air service to sparsely populated regions. There are two major objectives. The first is to examine those characteristics of sparsely populated areas which pertain to air transportation. This involves determination of geographical, commercial and population trends, as well as those traveler characteristics which affect the viability of air transport in the region. The second objective is to analyze the technical, economic and operational characteristics of low density air service. Two representative, but diverse arenas, West Virginia and Arizona, were selected for analysis: The results indicate that Arizona can support air service under certain assumptions whereas West Virginia cannot.
    Keywords: AIRCRAFT
    Type: NASA-CR-2142
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  • 64
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    A VTOL translational rate control system study on a six degrees-of-freedom motion simulator (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A linearized translational rate system for near hover flight was optimized on a large motion simulator under the constraints of no disturbances and limited control power. Both lateral and longitudinal modes were considered with the primary variables of investigation being control sensitivity and response stiffness and secondarily system damping. Yaw and height control characteristics were represented by an angular rate and acceleration system, respectively. General regions of desired sensitivity and stiffness for the longitudinal and lateral modes were determined under VFR conditions for both the rapid maneuver task and the station keeping/mild maneuver task.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62194
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  • 65
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    Effect of pictorial display configuration on the frequency of control reversals during aircraft landing approaches (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fixed-base simulator study to determine the effect of increased pictorial display realism on the frequency of control reversals made with an inside-out landing display was conducted. Display conditions included the effects of collimation and scale (head-up versus head-down presentation), horizon symbology (simple line versus white-black sky-ground surfaces), and ground plane realism (computer generated perspective versus a TV picture of a realistic model). The number of control reversals was moderately high on all displays. Control reversals to roll disturbances occurred nearly twice as frequently as reversals to either pitch or lateral rate disturbances. Though there were no significant differences among the numbers of small control reversals for the different displays, there was some evidence that this conclusion may not apply to large control reversals.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62191
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  • 66
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    A conceptual study of the rotor systems research aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analytical comparison of the two candidate Rotor Systems Research Aircraft (RSRA) configurations selected by the Government at the completion of Part 1 of the RSRA Conceptual Predesign Study is presented. The purpose of the comparison was to determine the relative suitability of both vehicles for the RSRA missions described in the Government Statement of Work, and to assess their versatility in the testing of new rotor concepts. The analytical comparison was performed primarily with regard to performance and stability and control. A weights, center-of-gravity, and inertia computation was performed for each iteration in the analysis process. The dynamics investigation was not concerned so much with a comparison of the two vehicles, but explored the dynamic problems attending operation of any RSRA operating with large rotor RPM and diameter ranges over large forward speed ranges. Several means of isolating in- and out-of-plane rotor vibrations were analyzed. An optimum isolation scheme was selected.
    Keywords: AIRCRAFT
    Type: NASA-CR-112157
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    Experimental investigation of an accelerometer controlled automatic braking system (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made to determine the feasibility of an automatic braking system for arresting the motion of an airplane by sensing and controlling braked wheel decelerations. The system was tested on a rotating drum dynamometer by using an automotive tire, wheel, and disk-brake assembly under conditions which included two tire loadings, wet and dry surfaces, and a range of ground speeds up to 70 knots. The controlling parameters were the rates at which brake pressure was applied and released and the Command Deceleration Level which governed the wheel deceleration by controlling the brake operation. Limited tests were also made with the automatic braking system installed on a ground vehicle in an effort to provide a more realistic proof of its feasibility. The results of this investigation indicate that a braking system which utilizes wheel decelerations as the control variable to restrict tire slip is feasible and capable of adapting to rapidly changing surface conditions.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6953 , L-8108
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  • 68
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    Rotor systems research aircraft of predesign study. Volume 1: Summary and conclusions (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are summarized of a study to develop a versatile research aircraft for flight testing a wide variety of advanced helicopter and compound rotor systems. The aircraft is required to accept these rotors with minimal changes in the basic vehicle. Rotors envisioned for testing include conventional rotors plus variable geometry, variable twist, variable diameter, coaxial, jet flap, circulation control, and slowed rotors. Various disc loadings would be accommodated. The aircraft must be configured to measure performance more accurately than past test vehicles. In addition, the aircraft would have a wing to off load the rotor while measuring performance during lightly loaded conditions. It would have variable drag and propulsive force so that the rotor can be tested while producing different values of horizontal force.
    Keywords: AIRCRAFT
    Type: NASA-CR-112152 , SER-50775-VOL-1
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  • 69
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    Three-track runway and taxiway profiles measured at international airports I and J (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Three-track runway and taxiway profiles are presented for use in studies of airplane response to ground roughness. Tabulated and plotted data for two international airports, (designated I and J), are included.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6932 , L-8485
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  • 70
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    SCIP2 flight instrumentation specification for parameter identification: User's guide (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: SCIP2 which is a digital computer program that can be used to investigate the effects of instrumentation errors on the accuracy of aircraft stability and control derivatives identified from flight test data is presented. The program is based on the assumptions that the aircraft differential equations of motion are linear and consist of small perturbations about a quasisteady flight condition. It is also assumed that a Newton-Raphson optimization technique is used for identifying the estimates of the parameters. A summary of the equations which are coded in the program are included.
    Keywords: AIRCRAFT
    Type: NASA-CR-112122
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  • 71
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    Dynamic stability derivatives at angles of attack from minus 5 deg to 90 deg for a variable-sweep fighter configuration with twin vertical tails (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in the Langley full-scale tunnel to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -5 deg to 90 deg for a variable-sweep fighter configuration with twin vertical tails. The study consisted of forced-oscillation tests of a 1/10-scale model of the airplane at a Reynolds number of 0.4 million based on the reference wing mean aerodynamic chord. Tests were conducted for wing sweep angles of 22 deg, 35 deg, 50 deg, and 68 deg, and the effects of the vertical and horizontal tails, wing leading-edge slats, nose-mounted canards, and frequency of the oscillation were also evaluated.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6909 , L-8426
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  • 72
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    Analysis of instrumentation error effects on the identification accuracy of aircraft parameters (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical investigation is presented of the effect of unmodeled measurement system errors on the accuracy of aircraft stability and control derivatives identified from flight test data. Such error sources include biases, scale factor errors, instrument position errors, misalignments, and instrument dynamics. Two techniques (ensemble analysis and simulated data analysis) are formulated to determine the quantitative variations to the identified parameters resulting from the unmodeled instrumentation errors. The parameter accuracy that would result from flight tests of the F-4C aircraft with typical quality instrumentation is determined using these techniques. It is shown that unmodeled instrument errors can greatly increase the uncertainty in the value of the identified parameters. General recommendations are made of procedures to be followed to insure that the measurement system associated with identifying stability and control derivatives from flight test provides sufficient accuracy.
    Keywords: AIRCRAFT
    Type: NASA-CR-112121
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  • 73
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    An engineering optimization method with application to STOL-aircraft approach and landing trajectories (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An optimization method has been developed that computes the optimal open loop inputs for a dynamical system by observing only its output. The method reduces to static optimization by expressing the inputs as series of functions with parameters to be optimized. Since the method is not concerned with the details of the dynamical system to be optimized, it works for both linear and nonlinear systems. The method and the application to optimizing longitudinal landing paths for a STOL aircraft with an augmented wing are discussed. Noise, fuel, time, and path deviation minimizations are considered with and without angle of attack, acceleration excursion, flight path, endpoint, and other constraints.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6978 , A-4323
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  • 74
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    Design evaluation criteria for commercial STOL transports (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Handling qualities criteria and operational performance margins have been determined for the landing phase of commercial short-takeoff-and-landing airplanes. The requirements are the result of a literature survey, analysis of areas found to be inadequately covered by current criteria, and a subsequent piloted simulator investigation of critical criteria requiring substantiation. Three complete simulator models were used, each describing the characteristics of a different high-lift system, the externally blown flap, the augmentor flap, and the internally blown flap. The proposed criteria are presented with substantiating discussions from currently available data or directly from the results of this simulation work where it is applicable.
    Keywords: AIRCRAFT
    Type: NASA-CR-114454 , D6-40409
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  • 75
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    Sonic-boom measurements for SR-71 aircraft operating at Mach numbers to 3.0 and altitudes to 24384 meters (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Sonic-boom pressure signatures produced by the SR-71 aircraft at altitudes from 10,668 to 24,384 meters and Mach numbers 1.35 to 3.0 were obtained as an adjunct to the sonic boom evaluation program relating to structural and subjective response which was conducted in 1966-1967 time period. Approximately 2000 sonic-boom signatures from 33 flights of the SR-71 vehicle and two flights of the F-12 vehicle were recorded. Measured ground-pressure signatures for both on-track and lateral measuring station locations are presented and the statistical variations of the overpressure, positive impulse, wave duration, and shock-wave rise time are illustrated.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6823 , L-8337
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  • 76
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    Analytical and experimental investigation of circulation control by means of a turbulent Coanda jet (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical and experimental investigation of circulation control on a circular cylinder by means of tangential blowing (Coanda effect) is presented. The analytical method developed has also been used to estimate the blowing coefficients required for achieving potential flow on airfoils with flaps. The analysis is presented for conditions for which the flow in the boundary layer ahead of the jet exit is turbulent. The turbulent boundary layer and the jet layer on the upper surface, and the turbulent boundary layer on the lower surface are computed by a multi-strip integral method. The region of integration is between the correponding transition and separation points on each surface. Longitudinal curvature effects, which give rise to a radial pressure gradient across the jet layer and to an additional adverse tangential pressure gradient just upstream of the separation point, are included in the jet layer analysis in an approximate manner. The longitudinal curvature effect is found to have a pronounced influence on the separation of the jet layer.
    Keywords: AIRCRAFT
    Type: NASA-CR-2114
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  • 77
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    Lateral stability and control derivatives of a jet fighter airplane extracted from flight test data by utilizing maximum likelihood estimation (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method of parameter extraction for stability and control derivatives of aircraft from flight test data, implementing maximum likelihood estimation, has been developed and successfully applied to actual lateral flight test data from a modern sophisticated jet fighter. This application demonstrates the important role played by the analyst in combining engineering judgment and estimator statistics to yield meaningful results. During the analysis, the problems of uniqueness of the extracted set of parameters and of longitudinal coupling effects were encountered and resolved. The results for all flight runs are presented in tabular form and as time history comparisons between the estimated states and the actual flight test data.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6905 , L-8378
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  • 78
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    Large scale wind tunnel investigation of a folding tilt rotor (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A twenty-five foot diameter folding tilt rotor was tested in a large scale wind tunnel to determine its aerodynamic characteristics in unfolded, partially folded, and fully folded configurations. During the tests, the rotor completed over forty start/stop sequences. After completing the sequences in a stepwise manner, smooth start/stop transitions were made in approximately two seconds. Wind tunnel speeds up through seventy-five knots were used, at which point the rotor mast angle was increased to four degrees, corresponding to a maneuver condition of one and one-half g.
    Keywords: AIRCRAFT
    Type: NASA-CR-114464 , D272-099-002
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  • 79
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    Community reaction to aircraft noise around smaller city airports (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of a study of community reaction to jet aircraft noise in the vicinity of airports in Chattanooga, Tennessee, and Reno, Nevada. These cities were surveyed in order to obtain data for comparison with that obtained in larger cities during a previous study. (The cities studied earlier were Boston, Chicago, Dallas, Denver, Los Angeles, Miami, and New York.) The purpose of the present effort was to observe the relative reaction under conditions of lower noise exposure and in less highly urbanized areas, and to test the previously developed predictive equation for annoyance under such circumstances. In Chattanooga and Reno a total of 1960 personal interviews based upon questionnaires were obtained. Aircraft noise measurements were made concurrently and aircraft operations logs were maintained for several weeks in each city to permit computation of noise exposures. The survey respondents were chosen randomly from various exposure zones.
    Keywords: AIRCRAFT
    Type: NASA-CR-2104
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  • 80
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    An analytical study of airplane-autopilot response to atmospheric turbulence (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical study has shown that, with proper selection of feedback gains, an automatic control system can reduce excursions in altitude of a jet transport flying in turbulence without increasing structural loads. The control system uses feedback of attitude-angle and pitch-rate signals to the elevator and uses feedback of altitude and altitude-rate signals to the throttle.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6869 , L-8140
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  • 81
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    Effects of an in-flight thrust reverser on the stability and control characteristics of a single-engine fighter airplane model (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The changes in thrust minus drag performance as well as longitudinal and directional stability and control characteristics of a single-engine jet aircraft attributable to an in-flight thrust reverser of the blocker-deflector door type were investigated in a 16-foot transonic wind tunnel. The longitudinal and directional stability data are presented. Test conditions simulated landing approach conditions as well as high speed maneuvering such as may be required for combat or steep descent from high altitude.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6886 , L-8395
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  • 82
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    Experimental verification of low sonic boom configuration (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A configuration designed to produce near field signature has been tested at M = 2.71 and the results are analyzed, by taking in account three-dimensional and second order effects. The configuration has an equivalent total area distribution that corresponds to an airplane flying at 60,000 ft. having a weight of 460,000 lbs, and 300 ft. length. A maximum overpressure of 0.95 lb/square foot has been obtained experimentally. The experimental results agree well with the analysis. The investigation indicates that the three-dimensional effects are very important when the measurements in wind tunnels are taken at small distances from the airplane.
    Keywords: AIRCRAFT
    Type: NASA-CR-2070 , NYU-AA-71-19
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  • 83
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    Wind-tunnel investigation at low speeds of a model of the Kestrel (XV-6A) vectored-trust V/STOL airplane (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Longitudinal and lateral stability data were obtained with the model out of and in ground effect over a moving ground plane for a range of model angles of attack and sideslip at various thrust coefficients. These data were taken primarily at thrust coefficients which simulate transition speeds on the airplane between hover and 200 knots. Some data, however, represent the effect of thrust deflection at speeds up to 350 knots. Also presented are the effects of control-surface deflections and interference between the jets and free stream.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6826 , L-8193
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  • 84
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    Flight measurements of buffet characteristics of the F-104 airplane for selected wing-flap deflections (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight program was conducted on the F-104 airplane to investigate the effects of moderate deflections of wing leading- and trailing-edge flaps on the buffet characteristics at subsonic and transonic Mach numbers. Selected deflections of the wing leading and trailing-edge flaps, individually and in combination, were used to assess buffet onset, intensity, and frequency; lift curves; and wing-rock characteristics for each configuration. Increased deflection of the trailing-edge flap delayed the buffet onset and buffet intensity rise to a significantly higher airplane normal-force coefficient. Deflection of the leading-edge flap produced some delay in buffet onset and the resulting intensity rise at low subsonic speeds. Increased deflection of the trailing-edge flap provided appreciable lift increments in the angle-of-attack range covered, whereas the leading-edge flap provided lift increments only at high angles-of-attack. The pilots appreciated the increased maneuvering envelope provided by the flaps because of the improved turn capability.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6943 , H-666
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  • 85
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    A Theoretical and Experimental Investigation of Flap-Lag Stability of Hingeless Helicopter Rotor Blades (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The stability of hingeless rotor blade oscillations in hover is examined theoretically using a simplified centrally-hinged, spring-restrained, rigid blade to approximate the deflections of actual elastic blades. The aerodynamic and inertial coupling between the flap and lead-lag degrees of freedom is primarily responsible for instability, however elastic coupling and kinematic pitch-lag coupling both exert a powerful influence on hingeless rotor blade stability. Experimental results obtained from a two-bladed 1.81m diameter model rotor designed for minimum elastic coupling have confirmed the results of linear theory. For this model configuration rotor blade stall at high pitch angles was found to counteract the destabilizing flap-lag coupling and increase the damping of lead-lag oscillations. It was possible to account for this effect with the theory by using drag data for stalled airfoils.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62179
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  • 86
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    Analysis of an electrohydraulic aircraft control surface servo and comparison with test results (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis of an electrohydraulic aircraft control-surface system is made in which the system is modeled as a lumped, two-mass, spring-coupled system controlled by a servo valve. Both linear and nonlinear models are developed, and the effects of hinge-moment loading are included. Transfer functions of the system and approximate literal factors of the transfer functions for several cases are presented. The damping action of dynamic pressure feedback is analyzed. Comparisons of the model responses with results from tests made on a highly resonant rudder control-surface servo indicate the adequacy of the model. The effects of variations in hinge-moment loading are illustrated.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6928 , H-629
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  • 87
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    An analysis of the takeoff and landing performance of a jet-powered STOL augmentor wing design (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary study of the takeoff and landing performance characteristics of a swept wing airplane with augmented jet flap, designed for STOL operation and low noise is presented. The study is based on aerodynamic data from wind tunnel tests of a large-scale swept augmentor wing model, scaled up to a 48,000 pound airplane. Engine characteristics are based on a turbo fan with a fan pressure ratio of 2.5 delivering the major portion of the thrust to the augmentor flap. A description of the overall airplane configuration, the propulsion system, and the use of the aerodynamics is presented. To assess the STOL performance of the airplane, takeoff and landing distances and flight path capabilities were computed at various flap deflections and thrust levels. After evaluating these results in terms of desired STOL performance with required margins, basic takeoff and landing configurations were chosen.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62176
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  • 88
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    Evaluation of minimum variance estimators for signal derivatives in real noise environments (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital filter has been developed to optimally estimate the rate of descent of an aircraft to permit all-weather operation. The filter was evaluated using recorded rate of descent information from flight instruments. The evaluation showed the filter to be superior to other systems especially when operated in turbulent air.
    Keywords: AIRCRAFT
    Type: NASA-CR-112146
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  • 89
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    Flight velocity influence on jet noise of conical ejector, annular plug and segmented suppressor nozzles (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An F106 aircraft with a J85-13 engine was used for static and flight acoustic and aerodynamic tests of a conical ejector, an unsuppressed annular plug, and three segmented suppressor nozzles. Static 100 ft. arc data, corrected for influences other than jet noise, were extrapolated to a 300 ft. sideline for comparison to 300 ft. altitude flyover data at M = 0.4. Data at engine speeds of 80 to 100% (max dry) static and 88 to 100% flight are presented. Flight velocity influence on noise is shown on peak OASPL and PNL, PNL directivity, EPNL and chosen spectra. Peak OASPL and PNL plus EPNL suppression levels are included showing slightly lower flight than static peak PNL suppression but greater EPNL than peak PNL suppression. Aerodynamic performance was as anticipated and closely matched model work for the 32-spoke nozzle.
    Keywords: AIRCRAFT
    Type: NASA-CR-120961
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  • 90
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    Coolant pressure and airflow distribution in a strut-supported transpiration-cooled vane for a gas turbine engine (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analysis to predict pressure and flow distribution in a strut-supported wire-cloth vane was developed. Results were compared with experimental data obtained from room-temperature airflow tests conducted over a range of vane inlet airflow rates from 10.7 to 40.4 g/sec (0.0235 to 0.0890 lb/sec). The analytical method yielded reasonably accurate predictions of vane coolant flow rate and pressure distribution.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6916 , E-6800
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  • 91
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    Examination of the collision force method for analyzing the responses of simple containment/deflection structures to impact by one engine rotor blade fragment (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An approximate collision analysis, termed the collision-force method, was developed for studying impact-interaction of an engine rotor blade fragment with an initially circular containment ring. This collision analysis utilizes basic mass, material property, geometry, and pre-impact velocity information for the fragment, together with any one of three postulated patterns of blade deformation behavior: (1) the elastic straight blade model, (2) the elastic-plastic straight shortening blade model, and (3) the elastic-plastic curling blade model. The collision-induced forces are used to predict the resulting motions of both the blade fragment and the containment ring. Containment ring transient responses are predicted by a finite element computer code which accommodates the large deformation, elastic-plastic planar deformation behavior of simple structures such as beams and/or rings. The effects of varying the values of certain parameters in each blade-behavior model were studied. Comparisons of predictions with experimental data indicate that of the three postulated blade-behavior models, the elastic-plastic curling blade model appears to be the most plausible and satisfactory for predicting the impact-induced motions of a ductile engine rotor blade and a containment ring against which the blade impacts.
    Keywords: AIRCRAFT
    Type: NASA-CR-120952 , ASRL-TR-154-6
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  • 92
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    Simulation study of the lift roll coupling problem for hovering VTOL aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of lift-roll coupling on the handling qualities of hovering VTOL aircraft using differential thrust for roll control were assessed in a piloted simulation study in the Ames six-degrees-of-freedom motion simulator. The configuration tested has three vertical thrust sources, one on the roll axis and two laterally displaced from the roll axis, with a thrust distribution of 25%/50%/25%. The outboard thrust sources were modulated to provide roll control whereas all three provided height control. Maximum thrust-to-weight ratio was varied together with a coupling parameter that combined roll-inertia, weight, and engine location. Results showed that handling qualities are affected not only by the occurrence of lift-roll coupling (dependent on both variables) but also by the severity of the coupling (dependent on the coupling parameter alone). However, the advantages of differential thrust for control can be retained with careful design.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6906 , A-3172
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  • 93
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    Concepts for a theoretical and experimental study of lifting rotor random loads and vibrations. Phase 6-B: Experiments with progressing/regressing forced rotor flapping modes (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A two bladed 16-inch hingeless rotor model was built and tested outside and inside a 24 by 24 inch wind tunnel test section at collective pitch settings up to 5 deg and rotor advance ratios up to .4. The rotor model has a simple eccentric mechanism to provide progressing or regressing cyclic pitch excitation. The flapping responses were compared to analytically determined responses which included flap-bending elasticity but excluded rotor wake effects. Substantial systematic deviations of the measured responses from the computed responses were found, which were interpreted as the effects of interaction of the blades with a rotating asymmetrical wake.
    Keywords: AIRCRAFT
    Type: NASA-CR-114481
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  • 94
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    Concepts for a theoretical and experimental study of lifting rotor random loads and vibrations. Phase 6-A: Effects of blade torsion, of blade flap bending flexibility and of rotor support flexibility on rotor stability and random response (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of lifting rotor blade torsion, blade flap bending flexibility and rotor support flexibility on rotor stability and random response are described. The subjects discussed are: (1) blade representation and method of analysis, (2) random gust response statistics for coupled torsion-flapping rotor blade vibrations, (3) flap bending corrections to the rigid blade analysis of lifting rotors, and (4) effects of rotor support flexibility. The response of linear periodically time varying systems to random excitation is examined.
    Keywords: AIRCRAFT
    Type: NASA-CR-114480
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  • 95
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    Predicted flight characteristics of the augmentor wing jet STOL research aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An existing deHavilland C-8A airplane has been modified into an augmentor wing flight test vehicle. Research objectives are to verify the augmentor flap concept and to produce data for STOL airworthiness criteria. The Modified C-8A provides the means for jet-STOL flight research down to a 60 knot approach speed. The airplane has a high thrust-to-weight ratio, high-lift flap system, vectored thrust, powerful flight controls, and lateral-directional stability augmentation system. Normal performance and handling qualities are expected to be satisfactory. Analysis and piloted simulator results indicate that stability and control characteristics in conventional flight are rated satisfactory. Handling qualities in the STOL regime are also generally satisfactory, although pilot workload is high about the longitudinal axis.
    Keywords: AIRCRAFT
    Type: NASA-CR-114463 , D6-40381
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  • 96
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    Effect of stabilization on VTOL aircraft in hovering flight (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A motion simulator study was conducted to determine the effects of roll and pitch stabilization on the handling qualities and control power requirements of VTOL aircraft during hover and short-distance maneuvering flight. Three levels of stabilization complexity were compared: (1) no stabilization, (2) rate stabilization, and (3) attitude stabilization. Control sensitivities and stabilization gains were optimized prior to comparison. Results are presented to show how the optimum systems were determined and how they compared with each other at different levels of control power. Comparisons were made both in calm air and in the presence of roll disturbances. Results indicate the attitude-stabilized system provides the best handling qualities for the least amount of control power.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-6900 , A-4015
    Format: application/pdf
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  • 97
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    Aerodynamic characteristics of a large-scale lift-engine fighter model with external swiveling lift-engines (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic characteristics of a six-engine (four lift, two lift-cruise) lift-engine model obtained in the Ames 40- by 80-foot wind tunnel are presented. The model was an approximate one-half scale representation of a lift-engine VTOL fighter aircraft with a variable-sweep wing. The four lift-engines were housed in the aft fuselage with the inlets located above the wing. Longitudinal and lateral-directional force and moment data are presented for a range of exhaust gas momentum ratios (thrust coefficients). Wind tunnel forward speed was varied from 0 to 140 knots corresponding to a maximum Reynolds number of 6.7 million. The data are presented without analysis.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62167
    Format: application/pdf
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  • 98
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    Noise measurements obtained during visual approach monitor evaluation in 747 aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are reported of acoustic measurements made on the 747 aircraft during visual approach monitor evaluation approaches. This display is designed to improve approach and landing precision under visual flight rule conditions. The purpose of the acoustic portion of the test was to measure, evaluate, and identify the noise levels during various types of aircraft approaches. Six noise measurement sites were positioned on the centerline of the approach ground track. The six noise measurement stations on the approach ground track were positioned between approximately 1 and 6 nautical miles from runway threshold. The 1-nautical mile point was chosen as the beginning of the ground track because it is specified as the approach measurement point in the FAA noise certification requirements. The 6-nautical mile point was chosen for its proximity to the point where the approach is initiated.
    Keywords: AIRCRAFT
    Type: NASA-CR-114478 , HRC-TR-S-213
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 99
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    Wind tunnel investigation of a large scale 35 deg swept wing jet transport model with an external blowing triple slotted flap (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted to determine the aerodynamic characteristics of a large-scale subsonic jet transport model with an externally jet-augmented flap system that would augment lift and provide direct-lift control. The model had a 35 deg swept wing of aspect ratio 7.82 and two side-by-side engines mounted on a single pylon under each wing close to the fuselage. The lift of the flap system was augmented by jet engine exhaust impingement on the triple-slotted flap surfaces. The rearmost flap provided direct lift control. Results were obtained for several combinations of flap deflections at gross thrust coefficients from 0 to 2.0. Three-component longitudinal data are presented with four engines operating. Limited longitudinal and lateral data are presented for asymmetric and symmetric thrust conditions with three engines operating. For the same overall flap deflection, lift coefficient and maximum lift coefficient were improved 13 and 7 percent compared to coefficients obtained with a double-slotted flap configuration. A maximum lift coefficient of 6.3 was obtained at a gross thrust coefficient of 2.0. At the same flap deflection lateral and directional trim moment requirements with an engine inoperative were reduced 55 and 33 percent, respectively, compared to those with the engines located farther outboard on the wing. Trim moment requirements in pitch were also reduced significantly. However, pitching-moment instability occurred and increased with gross thrust coefficient.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-2600 , A-3753
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 100
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    Design integration and noise studies for jet STOL aircraft. Volume 1: Program summary (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This program was undertaken to develop, through analysis, design, experimental static testing, wind tunnel testing, and design integration studies, an augmentor wing jet flap configuration for a jet STOL transport aircraft having maximum propulsion and aerodynamic performance with minimum noise generation. The program had three basic elements: (1) static testing of a scale wing section to demonstrate augmentor performance and noise characteristics; (2) two-dimensional wind tunnel testing to determine flight speed effects on performance; and (3) system design and evaluation which integrated the augmentor information obtained into a complete system and ensured that the design was compatible with the requirements for a large STOL transport having a 500-ft sideline noise of 95 PNdB or less. This objective has been achieved.
    Keywords: AIRCRAFT
    Type: NASA-CR-114471 , D6-40552-1-VOL-1
    Format: application/pdf
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