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  • Other Sources  (13)
  • NASA Technical Reports  (13)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (7)
  • AERODYNAMICS  (6)
  • 1
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    Transonic aerodynamic and aeroelastic characteristics of a variable sweep wing (1985)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The flow over the B-1 wing is studied computationally, including the aeroelastic response of the wing. Computed results are compared with results from wind tunnel and flight tests for both low-sweep and high-sweep cases, at 25.0 and 67.5 deg., respectively, for selected transonic Mach numbers. The aerodynamic and aeroelastic computations are made by using the transonic unsteady code ATRAN3S. Steady aerodynamic computations compare well with wind tunnel results for the 25.0 deg sweep case and also for small angles of attack at the 67.5 deg sweep case. The aeroelastic response results show that the wing is stable at the low sweep angle for the calculation at the Mach number at which there is a shock wave. In the higher sweep case, for the higher angle of attack at which oscillations were observed in the flight and wind tunnel tests, the calculations do not show any shock waves. Their absence lends support to the hypothesis that the observed oscillations are due to the presence of leading edge separation vortices and are not due to shock wave motion as was previously proposed.
    Keywords: AERODYNAMICS
    Type: AGARD Unsteady Aerodynamics-Fundamentals and Applications to Aircraft Dynamics; 15 p
    Format: text
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  • 2
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    Simulator study of the effect of control-system time delays on the occurrence of pilot-induced oscillations and on pilot tracking performance with a space-shuttle-orbiter configuration (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Using a six degree-of-freedom motion-base simulator, the effect of control-system time delays on the occurrence of pilot-induced oscillations (PIO's) on the vehicle handling qualities and on pilot tracking performance for a landing-approach configuration of the Space Shuttle orbiter was studied. A linearized math model was employed which represented a 300-knot orbiter with almost all time delays removed. Additional time delays were then inserted following the pilot's hand-controller signals. Only pitch and roll commands were used for vehicle control. The simulation employed an air to air tracking task as a means of emphasizing PIO tendencies. Two astronauts, two research pilots, and one simulation engineer served as test subjects. Results showed that PIO's occurred when the amount of added time delay approximated that existing for the orbiter configuration flown in the approach and landing tests. Increasing the amount of delay increased PIO occurrences and resulted in degraded tracking performance. Decreasing the amount of time delay eliminated the PIO's.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1588 , L-13131
    Format: application/pdf
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  • 3
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    Transonic aerodynamic and aeroelastic characteristics of a variable sweep wing (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The flow over the B-1 wing is studied computationally, including the aeroelastic response of the wing. Computed results are compared with results from wind tunnel and flight tests for both low-sweep and high-sweep cases, at 25.0 deg. and 67.5 deg., respectively, for selected transonic Mach numbers. The aerodynamic and aeroelastic computations are made by using the transonic unsteady code ATRAN3S. Steady aerodynamic computations compare well with wind tunnel results for the 25.0 deg. sweep case and also for small angles of attack at the 67.5 deg. sweep case. The aeroelastic response results show that the wing is stable at the low sweep angle for the calculation at the Mach number at which there is a shock wave. In the higher sweep case, for the higher angle of attack at which oscillations were observed in the flight and wind tunnel tests, the calculations do not show any shock waves. Their absence lends support to the hypothesis that the observed oscillations are due to the presence of leading edge separation vortices and are not due to shock wave motion as was previously proposed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86677 , A-85119 , NAS 1.15:86677
    Format: application/pdf
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  • 4
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    Simulator study of the effect of visual-motion time delays on pilot tracking performance with an audio side task (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of time delay was determined in the visual and motion cues in a flight simulator on pilot performance in tracking a target aircraft that was oscillating sinusoidally in altitude only. An audio side task was used to assure the subject was fully occupied at all times. The results indicate that, within the test grid employed, about the same acceptable time delay (250 msec) was obtained for a single aircraft (fighter type) by each of two subjects for both fixed-base and motion-base conditions. Acceptable time delay is defined as the largest amount of delay that can be inserted simultaneously into the visual and motion cues before performance degradation occurs. A statistical analysis of the data was made to establish this value of time delay. Audio side task provided quantitative data that documented the subject's work level.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1216 , L-11996
    Format: application/pdf
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  • 5
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    Evaluation of several secondary tasks in the determination of permissible time delays in simulator visual and motion cues (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of secondary tasks in determining permissible time delays in visual-motion simulation of a pursuit tracking task was examined. A single subject, a single set of aircraft handling qualities, and a single motion condition in tracking a target aircraft that oscillates sinusoidally in altitude were used. In addition to the basic simulator delays the results indicate that the permissible time delay is about 250 msec for either a tapping task, an adding task, or an audio task and is approximately 125 msec less than when no secondary task is involved. The magnitudes of the primary task performance measures, however, differ only for the tapping task. A power spectraldensity analysis basically confirms the result by comparing the root-mean-square performance measures. For all three secondary tasks, the total pilot workload was quite high.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1214 , L-12006
    Format: application/pdf
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  • 6
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    Fixed-base simulation study of decoupled controls during approach and landing of a STOL transport airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fixed-base visual simulation study has been conducted to evaluate the use of decoupled controls as a means for reducing pilot workload during approach and landing of an externally blown jet-flap short take-off and landing (STOL) transport. All six rigid-body degrees of freedom were employed with the aerodynamic characteristics based on wind-tunnel data. The primary piloting task was to use a flight director to capture and maintain a two-segment glide slope, with a closed-circuit television display of a STOL airport used during simulations of the flare and landing. The decoupled longitudinal controls used constant prefilter and feedback gains to provide steady-state decoupling of flight-path angle, pitch angle, and forward velocity. The pilots were enthusiastic about the decoupled longitudinal controls but believed the decoupled concept offered no significant advantage over conventional controls in the lateral mode.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7363 , L-8825
    Format: application/pdf
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  • 7
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    Comparison of analytical predictions of longitudinal short period pilot-induced oscillations with results from a simulation study of the space shuttle orbiter (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analytical analysis of conditions producing pilot induced oscillations (PIO's) was made for the space shuttle orbiter in a landing approach configuration for the task of milling the elevation angle of the line of sight to a target vehicle. The analysis yielded a value of PIO frequency and a value for the amount of total system time delay (pilot + control system) that can be tolerated before instability results. Calculations were performed showing the effect of varying the range to the target and of varying the handling qualities of the orbiter vehicle. Analytical predictions were compared with simulation results obtained using a visual motion simulator.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-83267 , L-14847 , NAS 1.15:83267
    Format: application/pdf
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  • 8
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    Model for the solution of supersonic viscous interaction effects on blunted cones (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Mar. 197
    Format: text
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  • 9
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    Static-pressure contours in the blade passage at the tip of several high Mach number rotors (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Static pressure contours of turbine rotor blade tips at high Mach numbers
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2170 , E-5875
    Format: application/pdf
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  • 10
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    Comparative performance tests on the Mod-2, 2.5-mW wind turbine with and without vortex generators (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A test program was conducted on the third Mod-2 unit at Goldendale, Washington, to systematically study the effect of vortex generators (VG's) on power performance. The subject unit was first tested without VG's to obtain baseline data. Vortex generators were then installed on the mid-blade assemblies, and the resulting 70% VG configuration was tested. Finally, vortex generators were mounted on the tip assemblies, and data was recorded for the 100% VG configuration. This test program and its results are discussed in this paper. The development of vortex generators is also presented.
    Keywords: AERODYNAMICS
    Type: DOE/NASA Workshop on Horizontal Axis Wind Turbine Technology; May 08, 1984 - May 10, 1984; Cleveland, OH; United States|DASCON Engineering, Collected Papers on Wind Turbine Technology; p 67-77
    Format: application/pdf
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