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  • Fluid Mechanics and Thermodynamics  (11)
  • Aircraft Design, Testing and Performance  (8)
  • 2020-2020
  • 1955-1959  (19)
  • 1957  (19)
Collection
Keywords
Years
  • 2020-2020
  • 1955-1959  (19)
Year
  • 1
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    Loads Due to Controls at Transonic and Low Supersonic Speeds (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Some results of recent experimental investigations at supersonic and transonic speeds are presented to show the present status in the estimation of load distributions on controls and adjacent wing surfaces resulting from the deflection of flap controls and spoiler controls. The results indicate that the development of methods for predicting loads associated with controls has not kept pace with the acquisition of experimental data. At low supersonic speeds sweeping the hinge line induces strong three-dimensional-flow characteristics which cannot be treated by the simplified methods previously developed for controls without sweep. At transonic speeds the estimation of loads associated with controls must usually be dependent upon experimental information inasmuch as the latest attempts to predict chordwise and spanwise loadings have met with only limited success.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-L57D26a
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  • 2
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    An Investigation at Low Speed of the Spin Instability of Mortar-Shell Tails (1957)
    In:  CASI
    Details
    Publication Date: 2019-05-10
    Description: An investigation was made in the Langley stability tunnel to study the influence of number of fins, fin shrouding, and fin aspect ratio on the spin instability of mortar-shell tail surfaces. It was found that the 12-fin tails tested spun less rapidly throughout the angle-of-yaw range than did the 6-fin tails and that fin shrouding reduced the spin encountered by a large amount.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L57E09a
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  • 3
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    Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7 (1957)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers based on momentum thickness were between 320 and 380 for the blunt cone. The model surface roughness was 25 rms microinches or greater. Turbulent heat transfer to the conical surface of the blunt cone at a Mach number of 4 was 30 percent less than that to the surface of the sharp cone. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-L57D04
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  • 4
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    Seat Design for Crash Worthiness (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study of many crash deceleration records suggested a simplified model of a crash deceleration pulse, which incorporates the essential properties of the pulse. The model pulse is considered to be composed of a base pulse on which are superimposed one or more secondary pulses of shorter duration. The results of a mathematical analysis of the seat-passenger deceleration in response to the airplane deceleration pulse are provided. On the basis of this information, presented as working charts, the maximum deceleration loads experienced by the seat and passenger in response to the airplane deceleration pulse can be computed. This maximum seat-passenger deceleration is found to depend on the natural frequency of the seat containing the passenger, considered as a mass-spring system. A method is presented that shows how to arrive at a combination of seat strength, natural frequency, and ability to absorb energy in deformation beyond the elastic limit that will allow the seat to serve without failure during an airplane deceleration pulse taken as the design requirement.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TR-1332
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  • 5
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    Free-Flight Skin Temperature and Pressure Measurements on a Slightly Blunted 25 Deg Cone-Cylinder-Flare Configuration to a Mach Number of 9.89 (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Skin temperatures and surface pressures have been measured on a slightly blunted cone-cylinder-flare configuration to a maximum Mach number of 9.89 with a rocket-propelled model. The cone had a t o t a l angle of 25 deg and the flare had a 10 deg half-angle. Temperature data were obtained at eight cone locations, four cylinder locations, and seven flare locations; pressures were measured at one cone location, one cylinder location, and three flare locations. Four stages of propulsion were utilized and a reentry type of trajectory was employed in which the high-speed portion of flight was obtained by firing the last two stages during the descent of the model from a peak altitude of 99,400 feet. The Reynolds number at peak Mach number was 1.2 x 10(exp 6) per foot of model length. The model length was 6.68 feet. During the higher speed portions of flight, temperature measurements along one element of the nose cone indicated that the boundary layer was probably laminar, whereas on the opposite side of the nose the measurements indicated transitional or turbulent flow. Temperature distributions along one meridian of the model showed the flare to have the highest temperatures and the cylinder generally to have the lowest. A maximum temperature of 970 F was measured on the cone element showing the transitional or turbulent flow; along the opposite side of the model, the maximum temperatures of the cone, cylinder, and flare were 545 F, 340 F, and 680 F, respectively, at the corresponding time.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-L57B18
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  • 6
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    A Fuselage Addition to Delay Drag-Rise Mach Number of Subsonic Airplanes at Lifting Conditions (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The addition of fuselage volume, concentrated on top of the forward portion of the fuselage, for the purpose of delaying the drag-rise Mach number of subsonic airplanes at lifting conditions is investigated. The additions have been designed on the basis of the area rule and other important considerations to provide greater practicability of application compared with shapings previously investigated. The addition delayed the drag-rise Mach number by an increment of approximately 0.03 for a configuration having a wing with moderate thickness and 35 deg of sweepback at a lift coefficient of 0.3. A lesser delay was obtained for a configuration with a thicker wing. The additions increase the nonlinearities of the variations of pitching moment with lift,
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L57H09b
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  • 7
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    Effect of Some External Crosswise Stiffeners on the Heat Transfer and Pressure Distribution on a Flat Plate at Mach Numbers of 0.77, 1.39, and 1.98. Coord. No. AF-AM-69 (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The heat transfer and pressures on the surfaces of several flat-plate models with various external crosswise stiffener arrangements are presented. The tests were made in a free jet at Mach numbers of 0.77, 1.39, and 1.98 for Reynolds numbers of 3 x 10(exp 6), 7 x 10(exp 6), and 14 x 10(exp 6), respectively, based on a length of 1 foot. The addition of external crosswise stiffeners to the flat-plate models caused large pressure and heat-transfer variations on the surfaces of the models.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-SL57E31a
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  • 8
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    On the Spectrum of Natural Oscillations of Two-Dimensional Laminar Flows (1957)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: In the investigation of stability of a two-dimensional laminar flow with respect to small disturbances, a disturbance of the stream function moving downstream (in the direction of the x-axis) by the "partial wave formula" is described.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA/TM-1417 , Zeitschrift fuer Angewandte mathematik und Mechanik (Magazine for Applied Mathematics and Mechanics); 34; 9-Aug; 344-357
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  • 9
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    The Principles of Turbulent Heat Transfer (1957)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The literature on turbulent heat transfer has in the course of years attained a considerable volume. Since this very complicated problem has not as yet found a complete solution, further studies in this field may be expected. The heat engineer must therefore accomodate himself to a constantly increasing number of theories and formulas. Since the theories generally start from hypothetical assumptions, and since they contain true and false assertions, verified knowledge and pure suppositions often being intermingled in a manner difficult to tell them apart, the specialist had difficulty in forming a correct evaluation of the individual studies. The need therefore arises for a presentation of the problem of turbulent heat transfer which is not initially bound by hypothetical assumptions and in which uninvestigated can be clearly distinguished form each other. Such a presentation will be given in the present treatment. Brief remarks with regard to the development of the theory of local heat transfer are included.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1408 , Archiv f. die Gesamte Waermetechnik; No. 6/7
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  • 10
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    Measurements of Heat Transfer and Boundary-Layer Transition on an 8-Inch-Diameter Hemisphere-Cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88 (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Measurements of aerodynamic heat transfer have been made along the hemisphere and cylinder of a hemisphere-cylinder rocket-propelled model in free flight up to a Mach number of 3.88. The test Reynolds number based on free-stream condition and diameter of model covered a range from 2.69 x l0(exp 6) to 11.70 x 10(exp 6). Laminar, transitional, and turbulent heat-transfer coefficients were obtained. The laminar data along the body agreed with laminar theory for blunt bodies whereas the turbulent data along the cylinder were consistently lower than that predicted by the turbulent theory for a flat plate. Measurements of heat transfer at the stagnation point were, in general, lower than the theory for stagnation-point heat transfer. When the Reynolds number to the junction of the hemisphere-cylinder was greater than 6 x l0(exp 6), the transitional Reynolds number varied from 0.8 x l0(exp 6) to 3.0 x 10(exp 6); however, than 6 x l(exp 6) when the Reynolds number to the junction was less, than the transitional Reynolds number varied from 7.0 x l0(exp 6) to 24.7 x 10(exp 6).
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-L57D04a
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  • 11
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    Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model between Mach Numbers of 0.81 and 1.64, TED No. NACA AD 399 (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A flight investigation was conducted to determine the effects of an inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model which was flight tested at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. Results indicate that the combined effects of the modified inlet and fully extended rocket racks on the trim lift coefficient and trim angle of attack were small between Mach numbers of 0.94 and 1.57. Between Mach numbers of 1.10 and 1.57 there was an average increase in drag coefficient of about o,005 for the model with modified inlet and extended rocket racks. The change in drag coefficient due to the inlet modification alone is small between Mach numbers of 1.59 and 1.64
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL57D30
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  • 12
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    Aerodynamic Forces on a Vibrating Unstaggered Cascade (1957)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The unsteady aerodynamic forces, [based on two-dimensional incompressible flow considerations], are determined for an unstaggered cascade, the blades of which are vibrating in phase in an approach flow parallel to the blades.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA/TM-1412 , Zeitschrift fuer Angewandte Mathematik und Mechanik (Magazine for Applied Mathematics and Mechanics); 35; 3; 81-88
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  • 13
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    Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120 (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions tested. An increase in lift-curve slope from 0.045 to 0.059 and an 11-percent rearward shift in aerodynamic-center location occurred with increases in Mach number from 0.60 to approximately 1.05. The zero-lift drag coefficient for the TF-102A airplane increased 145 percent between the Mach numbers of 0.85 and 1.075; the maximum lift-drag ratio decreased from 9.5 at a Mach number of 0.60 to 5.0 at Mach numbers above 1.025. There was little difference in the lift and pitching-moment characteristics and drag due to life between the TF-102A and F-102A configurations. However, as compared with the F-102A airplane, the zero-lift drag-rise Mach number for the TF-102A was reduced by at least 0.06, the zero-lift peak wave drag was increased 50 percent, and the maximum lift-drag ratio was reduced as much as 20 percent.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL57E22
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  • 14
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    Heat of Combustion of the Product Formed by the Reaction of Acetylene, Ethylene, and Diborane (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The net heat of combustion of the product formed by the reaction of diborane with a mixture of acetylene and ethylene was found to be 20,440 +/- 150 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and the combustion was believed to be 98 percent complete. The estimated net-heat of combustion for complete combustion would therefore be 20,850 +/- 150 Btu per pound.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-E53H18
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  • 15
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    Heat of Combustion of the Product Formed by the Reaction of Acetylene and Diborane (LFPL-CZ-3) (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The heat of combustion of the product formed by the reaction acetylene and diborane was found to be 20,100 +/- 100 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and chemical analyses both of the sample and of the combustion products indicated combustion in the bomb calorimeter to have been 97 percent complete. The estimated net heat of combustion for complete combustion would therefore be 20,700 +/- 100 Btu per pound.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-E53K10
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  • 16
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    Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specifications, but the ignition delay was almost twice the specified value of 0.040 second.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E57G29
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  • 17
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    Concluding Report of Free-Spinning, Tumbling, and Recovery Characteristics of a 1/18-Scale Model of the Ryan X-13 Airplane, Coord. No. AF-199 (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been completed in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine its spin, recovery, and tumbling characteristics, and to determine the minimum altitude from which a belly landing could be made in case of power failure in hovering flight. Model spin tests were conducted with and without simulated engine rotation. Tests without simulated engine rotation indicated two types of spins: one, a slightly oscillatory flat spin; and the other, a violently oscillatory spin. Tests with simulated engine rotation indicated that spins to the left were fast rotating and steep and those to the right were slow rotating and flat. The optimum technique for recovery is reversal of the rudder to against the spin and simultaneous movement of the ailerons to full with the spin followed by movement of the elevators to neutral after the spin rotation ceases. Tumbling tests made on the model indicated that although the Ryan X-13 airplane will not tumble in the ordinary sense (end-over-end pitching motion), it may instead tend to enter a wild gyrating'motion. Tests made to simulate power failure in hovering flight by dropping the model indicated that the model entered what appeared to be a right spin. An attempt should be made to stop this motion immediately by moving the rudder to oppose the rotation (left pedal), moving the ailerons to with the spin (stick right), and moving the stick forward after the spin rotation ceases to obtain flying speed for pullout. The minimum altitude required for a belly landing in case of power failure in hovering flight was indicated to be about 4,200 feet.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL57D11
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  • 18
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    Tensile Properties of Some Structural Sheet Materials Under Rapid-Heating Conditions (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of the NACA tests to determine the tensile strength of some structural sheet materials heated to failure at temperature rates from 0.2 deg. F to 100 deg F per second under constant load conditions are reviewed . Yield and rupture stresses obtained under rapid-heating conditions are compared with the results of conventional elevated-temperature tensile tests. The relation between rapid-heating tests, short-time creep tests, and conventional creep tests is discussed . The application of a phenomenological theory for calculating rapid-heating curves is shown. Methods are given for predicting yield and rupture stresses and temperatures from master curves and temperature-rate parameters
    Keywords: Aircraft Design, Testing and Performance
    Type: Fourth Sagamore Ordnance Materials Research Conference; Aug 21, 1957 - Aug 23, 1957; Raquette Lake, NY; United States
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  • 19
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    The Effect of Solid Admixtures on the Velocity of Motion of a Free Dusty Air Jet (1957)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In dusty air flows occurring in industrial practice in transport by air pressure of friable materials, in the drying, annealing, and so forth, of a pulverized solid mass in suspension, and in other processes, the concentration of solid particles usually has a magnitude of the order of 1 kg per 1 kg of air. At such a concentration, the ratio of the volume of the particles to the volume of the air is small (less than one-thousandth part). However, regardless of this, the presence of a solid admixture manifests itself in the rules for the velocity distribution of the air in a dusty air flow. As a result, the rules of velocity change are different for clean and for dusty air flows. The estimation of the influence of the admixture on the velocity of the motion of the flow presents a definitive interest. One of the attempts to estimate that influence on the axial velocity of a free axially symmetrical jet with admixtures was made by Abramovich. Abramovich assumed beforehand that the fine particles of the admixture in the jet are subject to the motion of the air (that is, that the velocity of the admixture is approximately equal to the local velocity of the air); he then took as the basis of his considerations, in solving the problem, the condition that the amount of motion of the two-phase jet must be constant.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1430 , Zhurnal Tekhnicheskoi Fiziki; XXI; 5; 1060-1063
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