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  • Chemistry  (2,576)
  • Aircraft Design, Testing and Performance  (20)
  • 1955-1959  (2,596)
  • 1956  (2,596)
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  • 1955-1959  (2,596)
Year
  • 1
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    Aeroelastic Problems of Airplane Design (1956)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The technical memorandum briefly summarizes the growth of interest in aeroelastic phenomena as aircraft speed increased and wing designs changed for faster aircraft. Different types of aircraft vibrations are then introduced, and the mathematical basis for the theory behind them is described. Special attention is given to static oscillations, wing flutter, and the flutter of skin panels. The last section of the memorandum deals with the prevention of flutter by design specifications.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1402 , Zeitschrift fuer Flugwissenschaften 3 Jahrgang, Heft 1; 1-18
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Safeguards Against Flutter of Airplanes (1956)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: This report is a complilation of practical rules, derived at the same time from theory and from experience, intended to guide the aeronautical engineer in the design of flutter-free airplanes. Rules applicable to the wing, the ailerons, flaps, tabs,tail surfaces, and fuselage are discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1423
    Format: application/pdf
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  • 3
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    On Landing Gear Stresses (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Information on landing gear stresses is presented on the following: vibratory phenomena, tangential forces applied to landing gear, fore and aft oscillations of landing gears, examples of fatigue failures, vibration calculations, and improvement of existing test equipment.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1422 , Sur les Sollicitations des Atterrisseurs; 25; 17-38
    Format: application/pdf
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  • 4
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    Research-Airplane-Committee Report on Conference on the Progress of the X-15 Project: A Compilation of the Papers Presented, Held at Langley Aeronautical Lab., Langley Field, VA on 25-26 October 1956 (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This document is a compilation of papers presented at the Conference on the Progress of the X-15 project held at the Langley Aeronautical Laboratory on 25-26 October 1956. The conference was held by the Research Airplane Committee of the U. S. Air Force, the U. S. Navy, and the National Advisory Committee for Aeronautics to report on the technical status of this research airplane. The papers were presented by members of the staffs of North American Aviation, Inc., Reaction Motors, Inc., and NACA.
    Keywords: Aircraft Design, Testing and Performance
    Type: Conference on the Progress of the X-15 Project; Oct 25, 1956 - Oct 26, 1956; Langley Field, VA; United States
    Format: application/pdf
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  • 5
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    An Experimental Investigation of Sting-Support Effects on Drag and a Comparison with Jet Effects at Transonic Speeds (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This paper presents the results of an investigation of sting-support interference on afterbody drag at transonic speeds. Stings with varying diameter, cone angle, and cylindrical length were tested at the rea r of a model with various afterbody shapes. The data were obtained at an angle of attack of O deg. and at Mach numbers from 0.80 to 1.10. It was found that, in general, the addition of a sting caused a drag reduction. A method is presented whereby approximate sting-interferen ce corrections may be made to models with afterbodies and sting suppo rts of similar size and scale to those of this paper provided the bou ndary layer is turbulent at the model base and the Reynolds numbers a re of the same order of magnitude. Reynolds number of the tests prese nted varied from 15.0 x 10 (exp 6) to 17.4 x 10 (exp 6) based on body length. Sting effects from this investigation are compared with data of jet effects on the same afterbodies. The results of this comparis on indicate that for the more gradually contoured afterbodies, a stin g shape can be found which will duplicate the jet effects, but that f or blunt afterbodies no solid sting shape will duplicate the jet effe cts.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L56F18a
    Format: application/pdf
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  • 6
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    Flight Investigation to Determine the Effect of Jet Exhaust on Drag, Trim Characteristics, and Afterbody Pressures of a 0.125-Scale Rocket Model of the Mcdonnell F-101A Airplane (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A flight investigation was conducted to determine the effect of jet exhaust on the drag, trim characteristics, and afterbody pressures on a 0.125-scale rocket model of the McDonnell F-101A airplance. Power-off data were obtained over a Mach number range of 1.04 to 1.9 and power-on data were obtained at a Mach number of about 1.5. The data indicated that with power-on the change in external drag coefficient was within the data accuracy and there was a decrease in trim angle of attack of 1.27 degrees with a corresponding decrease of 0.07 in lift coefficient. Correspondingly, pressure coefficients on the side and bottom of the fuselage indicated a positive increment near the jet exit. As the distance downstream of the jet exit increased, the increment on the bottom of the fuselage increased, whereas the increments on the side decreased to a negative peak.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL56B03
    Format: application/pdf
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  • 7
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    Altitude Acceleration Investigation of the RA-14 Avon Turbojet Engine (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: As a part of this investigation, the acceleration characteristics of the engine, using the standard engine fuel-control system, were obtained for conditions simulating flight at altitudes of 35,000 and 50,000 feet with a flight Mach number of 0.4. Rapid and wave-off type accelerations were made at each flight condition, and the transient performance of the engine was recorded with a multiple-channel oscillograph. The parameters are presented graphically in the form of time histories, augmented by short segments of the oscillograph recordings, in order to more completely describe the behavior of the engine parameters when surge was encountered.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E56C01
    Format: application/pdf
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  • 8
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    Longitudinal and Lateral Stability Characteristics of a 0.04-Scale Model of the Lockheed F-104A Airplane at Mach Numbers of 1.82 and 2.01. Coord. No. AF-245 (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation has been made in the Langley 4 by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the longitudinal and lateral static-stability characteristics of a 0.04-scale model of the Lockheed F-104A airplane. The effects of a modified vertical tail, several ventral-fin arrangements, and several external store arrangements were also determined. The tests were made at Reynolds numbers of 1.02 (exp 6) and 1.382 (exp 6), respectively, based on the wing mean geometric chord. The tests were made of combined angles of attack and sideslip that varied from about -4 deg. to about 20 deg.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL56H06
    Format: application/pdf
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  • 9
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    The High-Speed Longitudinal Stability and Control of the Bell P-39N-1 Airplane as Calculated from Propeller-Off Tests of a 0.35-Scale Model (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This report presents the results of tests of a .35-scale model of the Bell P-39N-1 airplane. Included are the longitudinal-stability and -control characteristics of the airplane as indicated by tests of the model equipped with each of two different sets of elevators. The results indicate good longitudinal stability and control throughout the speed range encounterable in flight. The variation of estimated stick force with speed was less when the model was equipped with elevators constructed to the theoretical design dimensions than when equipped with elevators as built to scale from measurements of the corresponding parts of the actual airplane. The predicted stick forces required to produce the normal accelerations attainable in flight are within the limits specified by the Army Air Forces.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA6L27
    Format: application/pdf
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  • 10
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    The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390 (1956)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined. The results indicate that for a horizontal-tail incidence of -10 deg the trim lift coefficient varied from 0.29 at a Mach number of 1.61 to 0.23 at a Mach number of 2.01 with a corresponding decrease in lift-drag trim from 3.72 to 3.15. Stick-position instability was indicated in the low-supersonic-speed range. A photographic-type nose modification resulted in slightly higher values of minimum drag coefficient but did not significantly affect the static stability or lift-curve slope. The minimum drag coefficient for the complete model with the production nose remained essentially constant at 0.047 throughout the Mach number range investigated.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL56E24
    Format: application/pdf
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