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  • 1
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    Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the Chance Vought F8U-1P Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An investigation has been made in the Langley 20-foot free-spinning tunnel on a 1/25-scale dynamic model to determine the spin and recovery characteristics of the Chance Vought F8U-1P airplane. Results indicated that the F8U-IP airplane would have spin-recovery characteristics similar to the XF8U-1 design, a model of which was tested and the results of the tests reported in NACA Research Memorandum SL56L31b. The results indicate that some modification in the design, or some special technique for recovery, is required in order to insure satisfactory recovery from fully developed erect spins. The recommended recovery technique for the F8U-lP will be full rudder reversal and movement of ailerons full with the spin (stick right in a right spin) with full deflection of the wing leading- edge flap. Inverted spins will be difficult to obtain and any inverted spin obtained should be readily terminated by full rudder reversal to oppose the yawing rotation and neutralization of the longitudinal and lateral controls. In an emergency, the same size parachute recommended for the XFBU-1 airplane will be adequate for termination of the spin: a stable parachute 17.7 feet in diameter (projected) with a drag coefficient of 1.14 (based on projected diameter) and a towline length of 36.5 feet.
    Keywords: Aerodynamics
    Type: NASA-TM-SX-196 , L-714 , NASA-AD-3137
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Free-Spinning Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395 (1955)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine spin and recovery characteristics and the minimum-size parachute required to satisfactorily terminate the spin in an emergency. Results obtained to date are presented herein. Test results indicate that it may be difficult to obtain an erect or inverted spin on the airplane, but, if a spin is obtained, the spin will be very oscillatory and recovery from the developed erect spin by rudder reversal may not be possible. The lateral controls will have no appreciable effect on recoveries from erect.spins. Recovery from the inverted spin by merely neutralizing the rudder will be satisfactory. After recoveries by rudder reversal and after recoveries from spins without control movement (no spins), the model oftentimes rolled very rapidly about the X-axis. Based on limited preliminary tests made in this investigation to make the model recover satisfactorily, it appears that canards near the nose of the airplane or differentially operated horizontal tails may be utilized to provide rapid recoveries. The parachute test results indicate that an 11-foot-diameter (laid-out-flat) parachute with a drag coefficient of 0.650 (based on the laid- out-flat diameter) and with a towline length equal to the wing span is the minimum-size parachute required to satisfactorily terminate an erect or inverted spin in an emergency.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55G20 , Rept-5121
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Free-Spinning and Recovery Characteristics of a 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 is being conducted in the Langley 20-foot free-spinning tunnel on a l/18 scale model of the Ryan X-13 airplane to determine its spin and recovery characteristics. The spin and recovery characteristics determined to date are presented in this report.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55H08 , Rept-5145
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Free-Spinning-Tunnel Investigation of a 1/17 Scale Model of the Cessna T-37A Airplane (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Results of an investigation of a dynamic model in the Langley 20-foot free-spinning tunnel are presented. Erect spin and recovery characteristics were determined for a range of mass distributions and center-of-gravity positions. The effects of lateral displacement of the center of gravity, engine rotation, nose strakes, and increased rudder area were investigated.
    Keywords: Aerodynamics
    Type: NASA-MEMO-3-1-59L , AF-AM-42 , L-237
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Free-Spinning-Tunnel Investigation of a 1/40-Scale Model of the McConnell F-101A Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation has been made in the Langley 20-foot free-spinning tunnel of a 1/40-scale model of the McDonnell F-101A airplane to alleviate the unfavorable spinning characteristics encountered with the airplane. The model results indicate that a suitable strake extended on the inboard side of the nose of the airplane (right side in a right spin) in conjunction with the use of optimum control recovery technique will terminate spin rotation of the airplane. It may be difficult to recover from subsequent high angle-of-attack trimmed flight attitudes even by forward stick movement. The optimum spin-recovery control technique for the McDonnell F-101A is simultaneous full rudder reversal to against the spin and aileron movement to full with the spin (stick full right in a right erect spin) and forward movement of the stick immediately after rotation stops.
    Keywords: Aerodynamics
    Type: NASA-MEMO-3-14-59L , AF-AM-87
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the North American T2J-1 Airplane (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation has been made in the Langley 20-foot free-spinning tunnel to determine the erect and inverted spin and recovery characteristics of a 1/20-scale dynamic model of the North American T2J-1 airplane. The model results indicate that the optimum technique for recovery from erect spins of the airplane will be dependent on the distribution of the disposable load. The recommended recovery procedure for spins encountered at the flight design gross weight is simultaneous rudder reversal to against the spin and aileron movement to with the spin. With full wingtip tanks plus rocket installation and full internal fuel load, rudder reversal should be followed by a downward movement of the elevator. For the flight design gross weight plus partially full wingtip tanks, recovery should be attempted by simultaneous rudder reversal to against the spin, movement of ailerons to with the spin, and ejection of the wing-tip tanks. The optimum recovery technique for airplane-inverted spins is rudder reversal to against the spin with the stick maintained longitudinally and laterally neutral.
    Keywords: Aerodynamics
    Type: NASA-TM-SX-245 , L-872 , NASA-AD-3136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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