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  • Aircraft Design, Testing and Performance  (10)
  • 1990-1994
  • 1955-1959  (10)
  • 1955  (10)
  • 1
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    Unknown
    Aerodynamic Characteristics of Various Configurations of a Model of a 45 Degree Swept-wing Airplane at a Mach Number of 2.01 (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted at the Langley 4- by 4-foot supersonic pressure tunnel at a Mach nmber of 2.01 to determine the aerodynamic characteristics of several configurations of a model of a 45 deg swept-wing airplane. The basic configuratin had a wing with 45 deg sweepback at the quarter-chord line, aspect ration 3.2, taper ration 0.468, NACA 65A005.5 sections just outboard of the inlet and NACA 65A003.7 sections at the tip. The wing was mounted slightly above the body center line and an all-movable horizantal tail was located slightly below the extended chord line of the wing. Tre design incorporated twin wing-root supersonic inlets ducted to a single exit at the base of the fuselage. The configurations investigated included an extended nose length, a bumped-fuselage afterbody, an inlet droop, an lncreased wing aspect ratio, and a revised canopy shape. Configurations employing the wing of increased aspect ratio of 3.7, which constituted the bulk of the tests, produced about a 10-percent increase in lift and in longitudinal stability as compared with the basic wing of aspect ratio 3.2. There was a slight but masurable increase in minimum drag and maximum lift-drag ratio.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L54J08
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of the Sidewinder Missile at Mach Numbers from 1.2 to 2.1 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: At the request of the Bureau of Ordnance, Department of the Navy, the Langley Pilotless Aircraft Research Division has initiated a program to investigate the general aerodynamic characteristics of the Naval Ordnance Test Station's SIDEWINDER missile. The model used in the flight test presented herein was a full-scale, rocket-propelled test vehicle. This paper presents the results from a flight test investigation using the pulsed-control technique to determine the static and dynamic longitudinal stability and control derivatives and drag data for a canard-missile configuration. The methods for obtaining these data are presented in references 1 and 2. This investigation was conducted at a small angle-of-attack range and for a Mach number range of 1.2 to 2.1. The model used in this investigation was flight-tested at the Langley Pilotless Aircraft Research Station at Wallops Island, Va.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL55K16
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Free-Spinning-Tunnel Investigation of a 0.034-Scale Model of the Production Version of the Chance Vought F7U-3 Airplane, TED No. NACA AD 3103 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of a 0.034-scale model of the production version of the Chance Vought F7U-3 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The inverted and erect spin and recovery characteristics of the model were determined for the combat loading with the model in the clean condition and the effect of extending slats was investigated. A brief investigation of pilot ejection was also performed. The results indicate that the inverted spin-recovery characteristics of the airplane will be satisfactory by full rudder reversal. If the rudders can only be neutralized because of high pedal forces in the inverted spins, satisfactory recovery will be obtained if the auxiliary rudders can be moved to neutral or against the spin provided the stick is held full forward. Optimum control technique for satisfactory recovery from erect spins will be full rudder reversal in conjunction with aileron movement to full with the spin (stick right in a right spin). Extension of the slats will have a slightly adverse effect on recoveries from (1 inverted spins but will have a favorable effect on recoveries from erect spins. The results of brief tests indicate that if a pilot is ejected during a spin while a spin-recovery parachute is extended and fully inflated, he will probably clear the tail parachute.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL55G15 , Rept-5115
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Ditching Investigation of a 1/12-Scale Model of the Douglas F3D-2 Airplane, TED No. NACA DE 381 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of a 1/12- scale dynamically similar model of the Douglas F3D-2 airplane was made in calm water to observe the ditching behavior and to determine the safest procedure for making an emergency water landing. Various conditions of damage were simulated to determine the behavior which probably would occur in a full-scale ditching. The behavior of the model was determined from motion-picture records, time- history acceleration records, and visual observations. It was concluded that the airplane should be ditched at a medium high attitude of about 8 degrees with the landing flaps down 40 degrees. In calm water the airplane will probably make a smooth run of about 550 feet and will have a maximum longitudinal deceleration of about 3g. The fuselage bottom will probably be damaged enough to allow the fuselage to fill with water very rapidly.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL52J30
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Ditching Investigation of a 1/11-Scale Model of the Chance Vought F7U-3 Airplane, TED NO. NACA DE 360 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was made of a 1/11-scale dynamically similar model of the Chance Vought F7U-3 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tabular form, sequence photographs, time-history acceleration curves, and plots of attitude change against time after contact. From the results of the investigation, it was concluded that the airplane should be ditched at the lowest speed and highest attitude consistent with adequate control. The aft part of the fuselage and the main landing-gear doors will probably be damaged. In a calm-water ditching under these conditions the airplane will probably skip slightly and then porpoise for the remainder of the run. Maximum longitudinal decelerations will be about 3 1/2g and maximum normal accelerations will be about 7g in a landing run of about 500 feet.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL52K07A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Emergency Spin-Recovery Device for the 1/18-Scale Model of the Ryan X-13 Airplane as Determined from Tests in the Langley 20-Foot Free-Spinning Tunnel (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine the size parachute required for emergency-spin recovery during demonstration spins. Test results for erect spins indicate that a stable 12.73-foot-diameter parachute with a drag coefficient of 1.11 (based on the 12.73-foot projected diameter) is the minimum size required to insure satisfactory recovery in an emergency. The use of a stable parachute is recommended. Test results for inverted spins indicate that the l2.75-foot-diameter parachute is also satisfactory to terminate inverted spins.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL55A25
    Format: application/pdf
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  • 7
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    Free-Spinning-Tunnel Investigation to Determine the Effect of Spin-Recovery Rockets and Thrust Simulation on the Recovery Characteristics of a 1/21-Scale Model of the Chance Vought F7U-3 Airplane, TED No. NACA AD 3103 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of a l/21-scale model of the Chance Vought F7U-3 airplane in the co&at-load- condition has been conducted in the Langley 20-foot free-spinning tunnel, The recovery characteristics of the model were determined by use of spin-recovery rockets for the erect and inverted spinning condition. The rockets were so placed as to provide either a yawing or rolling moment about the model center of gravity. Also included in the investigation were tests to determine the effect of simulated engine thrust on the recovery characteristics of the model. On the basis of model tests, recoveries from erect and inverted spins were satisfactory when a yawing moment of 22,200 foot-pounds (full scale) was provided against the spin by rockets attached to the wing tips; the anti-spin yawing moment was applied for approximately 9 seconds, (full scale). Satisfactory recoveries were obtained from erect spins when a rolling moment of 22,200 foot-pounds (full scale) was provided with the spin (rolls right wing down in right spin). Although the inverted spin was satisfactorily terminated when a rolling moment of equal magnitude was provided, a roll rocket was not considered to be an optimum spin-recovery device to effect recoveries from inverted spins for this airplane because of resulting gyrations during spin recovery. Simulation of engine thrust had no apparent effect on the spin recovery characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL55A04
    Format: application/pdf
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  • 8
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    Transonic Zero-Lift Drag Tests of Four Equivalent-Body-of-Revolution Models Representing Variations of the Convair F-102 Airplane (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Four 0.01643-scale equivalent-body-of-revolution models, designed to aid in the evaluation of the relative merits of various degrees of redesign of the existing (1955) Convair F-102 airplane, were launched from the helium gun at Wallops Island, Va., to determine their zero-lift drag at Mach numbers from 0.8 to 1.3. The data are presented with only sufficient analysis to validate their general subsonic level. Estimated values of the friction drag are presented at all Mach numbers to allow a comparison of the pressure drag values alone.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL55J31a , Rept-5246
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Component Performance Investigation of J71 Type II Turbines V - Internal Flow Conditions of J71 Type IIA Turbine (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An experimental investigation of the J71 Type IIA turbine was conducted at the equivalent design speed and work output. The design stagework distribution was closely approached, although the design vector diagram was not attained. Efficiencies of 0.904, 0.851, and 0.806 were obtained for the first, second, and third stages, respectively. Losses occurred near the hub and tip for all three rotors. The third-stage losses, however, were significantly greater than those of either the first or second stage.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E55H05
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Lateral Stability and Control Measurements of a 0.0858-Scale Model of the Lockheed XF-104 Airplane at Transonic Speeds (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation of the lateral stability and control effectiveness of a 0.0858-scale model of the Lockheed XF-104 airplane has been conducted in the Langley 16-foot transonic tunnel. The model has a low aspect ratio, 3.4-percent-thick wing with negative dihedral. The horizontal tail is located on top of the vertical tail. The investigation was made through a Mach number range of 0.80 to 1.06 at sideslip angles of -5 deg. to 5 deg. and angles of attack from 0 deg. to 16 deg. The control effectiveness of the aileron, rudder, and yaw damper were determined through the Mach number and angle-of-attack range. The results of the investigation indicated that the directional stability derivative was stable and that positive effective dihedral existed throughout the lift-coefficient range and Mach number range tested. The total aileron effectiveness, which in general produced favorable yaw with rolling moment, remained fairly constant for lift coefficients up to about 0.8 for the Mach number range tested. Yawing-moment effectiveness of the rudder changed little through the Mach number range. However, the yaw damper effectiveness decreased about 30 percent at the intermediate test Mach numbers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL55F08
    Format: application/pdf
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