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  • 1
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    Flight-Measured Aerodynamic Loads on a 0.92 Aspect Ratio Lifting Surface (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Ventral fin loads, expressed as normal force coefficients, bending moment coefficients, and torque coefficients, were measured during flight tests of a YF-12A airplane. Because of the proximity of the ventral fin to the ailerons, the aerodynamic loads presented were the result of both sideslip loads and aileron crossflow loads. Aerodynamic data obtained from strain gage loads instrumentation and some flight pressure measurements are presented for several Mach numbers ranging from 0.70 to 2.00. Selected wind tunnel data and results of linear theoretical aerodynamic calculations are presented for comparison.
    Keywords: AERODYNAMICS
    Type: YF-12 Experiments Symp., Vol. 1; p 73-91
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Effect of winglets on a first-generation jet transport wing. 4: Stability characteristics for a full-span model at Mach 0.30 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The static longitudinal and lateral directional characteristics of a 0.035 scale model of a first generation jet transport were obtained with and without upper winglets. The data were obtained for take off and landing configurations at a free stream Mach number of 0.30. The results generally indicated that upper winglets had favorable effects on the stability characteristics of the aircraft.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1119 , L-11705
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Models and techniques for evaluating the effectiveness of aircraft computing systems (1977)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Models, measures and techniques were developed for evaluating the effectiveness of aircraft computing systems. The concept of effectiveness involves aspects of system performance, reliability and worth. Specifically done was a detailed development of model hierarchy at mission, functional task, and computational task levels. An appropriate class of stochastic models was investigated which served as bottom level models in the hierarchial scheme. A unified measure of effectiveness called 'performability' was defined and formulated.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145270 , SEL-111 , SASR-2
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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