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  • 1
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    Aerodynamic characteristics of the planetary atmosphere experiments test entry probe (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The aerodynamic characteristics of the Planetary Atmosphere Experiments Test entry probe were determined experimentally in ballistic range tests over a wide range of Mach and Reynolds numbers, and were compared with full-scale flight results. The ground facility data agreed with the full-scale data within 2 to 3% in drag coefficient, and within 5 to 10% in static stability, at the higher Mach numbers. Comparisons of the flight data with conventional wind-tunnel data indicated a significant disagreement in drag coefficient in the transonic speed range suggestive of important sting or wall interference effects. Variations in drag coefficient with Mach number were very small hypersonically, but variations with Reynolds number were of the order of 15% at a free-stream Mach number of 13 over the Reynolds number range from 10,000 to 1,000,000. Variations in the lift and static-stability curves with Mach number and Reynolds number were also defined.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 12; Jan. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flying-qualities criteria for wings-level-turn maneuvering during an air-to-ground weapon delivery task (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A moving base simulator experiment demonstrated that a wings-level-turn control mode improved flying qualities for air to ground weapon delivery compared with those of a conventionally controlled aircraft. Evaluations of criteria for dynamic response for this system have shown that pilot ratings correlate well on the basis of equivalent time constant of the initial response. Ranges of this time constant, as well as digital system transport delays and lateral acceleration control authorities that encompassed level 1 through 3 handling qualities, were determined.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-81266 , A-8481
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Wake vortex encounter hazards criteria for two aircraft classes (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted using a piloted, motion-base simulator to determine wake vortex hazard criteria for two classes of jet transport aircraft. A light business jet and a large multiengine jet transport were represented respectively. The hazard boundaries were determined in terms of the maximum bank angle due to the vortex encounter. Upsets as small as 7 deg in bank angle were considered to be hazardous at breakout altitude (200 ft (61.0 m)) for Instrument Flight Rule (IFR) and at 50 ft (15.2 m) for Visual Flight Rule (VFR) for both aircraft classes. Proximity to the ground was the primary reason for a hazardous rating. This was reflected in the reduction in the maximum bank angle at the hazard boundary and in more consistent ratings as altitude was decreased.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-TM-X-73113 , FAA-RD-75-206 , A-6493
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Hazard criteria for wake vortex encounters (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A piloted, motion-base simulation was conducted to evaluate the ability of simulators to produce realistic vortex encounters and to develop criteria to define hazardous encounters. Evaluation of the simulation by pilots experienced in vortex encounters confirmed the capability of the simulator to realistically reproduce wake vortex encounters. A boundary for encounter hazard based on subjective pilot opinion was identified in terms of maximum bank angle. For encounter altitudes from 200 to 500 ft (61.0 to 152.4 m), tentative hazard criteria established for visual flight conditions indicated that the acceptable upset magnitude increased nearly linearly with increasing altitude. The data suggest that the allowable upsets under instrument conditions no greater than 50 percent of that allowable under visual conditions.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-TM-X-62473 , A-6232
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Effectiveness of Several Control Arrangements on a Mercury-Type Capsule (1961)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Trim effectiveness of aerodynamic control flaps on Mercury-type capsule
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-579
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Viking entry vehicle aerodynamics at m equals 2 in air and some preliminary test data for flight in CO2 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The static and dynamic aerodynamic characteristics of the Viking entry vehicle were determined experimentally in free flight in air at a Mach number near 2. Preliminary results were also obtained in CO2 at M infinity = 11. The low speed tests in air confirmed a region of dynamic instability previously observed. The instability was greatest at the smallest pitch amplitudes but decreased with increasing amplitude until a limit cycle was reached at about 8 deg. The tests in CO2 indicated increased drag coefficients of 3 percent with respect to those in air. Errors in the drag coefficient of this magnitude would significantly affect the reconstruction of the Martian atmosphere during entry of the Viking spacecraft.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7974 , A-4825
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Aerodynamics of Mars entry probe-lander configurations at a Mach number of 10 (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamics of Mars entry probe lander configurations at Mach 10
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-5608 , A-3334
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Transonic static- and dynamic-stability characteristics of two large-angle spherically blunted high-drag cones (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Transonic static and dynamic stability of large angle spherically blunted high-drag cones
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 70-564 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, ATMOSPHERIC FLIGHT MECHANICS CONFERENCE; May 13, 1970 - May 15, 1970; TULLAHOMA, TN
    Format: text
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  • 9
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    Hazard criteria for wake vortex encounters (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Piloted six-degrees-of-freedom motion simulator investigations were conducted at the NASA Ames Research Center to determine criteria relating the hazard posed by a wake vortex encounter to the response of the encountering airplane. These investigations demonstrated that wake vortex encounters can be realistically reproduced on a simulator, established that the maximum bank angle due to the encounter provides the best correlation with the pilot's subjective assessment of the hazard, and determined hazard boundaries in terms of maximum bank angle for two classes of jet transport aircraft.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Atmospheric Flight Mechanics Conference; Jun 07, 1976 - Jun 09, 1976; Arlington, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Dynamics of high drag probe shapes at transonic speeds (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Determination of transonic aerodynamic characteristics of spherically blunted 55 and 60 degree half-angle cones in ballistic range tests
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6489 , A-3613
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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