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  • Aircraft Stability and Control  (2)
  • Spacecraft Design, Testing and Performance  (1)
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  • 1
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    Unknown
    Predicted Shock Envelopes about Two Types of Vehicles at Large Angles of Attack (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Methods based on oblique - and normal-shock relationships and the continuity of mass flow through suitably chosen volume elements between the shock and body were developed t o predict shock envelopes about two types of vehicles being considered for atmosphere entry. One type is a high-drag capsule shape. The other type is essentially a slender tri- angular wing capable of providing high lift or high drag, depending on the angle of attack. Predicted and measured shock envelopes were compared f o Mach number range of 3 to 15 for vehicles at high angles of attack; good agreement was found. Most of the available experimental data were in a speed and temperature range in which no important real-gas effects occurred.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-TN-D-860 , A-491
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Estimation of Directional Stability Derivatives at Small Angles and Subsonic and Supersonic Speeds (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Methods are presented for estimating the directional stability derivative increments contributed by the stabilizing surfaces of subsonic and supersonic aircraft. These methods are strictly applicable at zero angle of attack and small angles of sideslip. The procedure of totaling the incremental coefficients to obtain an estimation of the total empennage side-force and yawing-moment coefficient derivatives is also shown, together with numerical examples. A correlation is presented between estimated and experimental incremental coefficients which indicates that the methods of this report generally estimate the increment of side force gained by the addition of a panel to within +/-10 percent of the experimental value while the yawing-moment increment is generally estimated to within +/-20 percent. This is true for both subsonic and supersonic Mach numbers. An example application of the methods to one of the problems in directional stability, that of minimizing the effect of Mach number on the side-force coefficient derivative of the empennage, is discussed.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-2-58A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Estimation of Directional Stability Derivatives at Moderate Angles and Supersonic Speeds (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A study of some of the important aerodynamic factors affecting the directional stability of supersonic airplanes is presented. The mutual interference fields between the body, the lifting surfaces, and the stabilizing surfaces are analyzed in detail. Evaluation of these interference fields on an approximate theoretical basis leads to a method for predicting directional stability of supersonic airplanes. Body shape, wing position and plan form, vertical tail position and plan form, and ventral fins are taken into account. Estimates of the effects of these factors are in fair agreement with experiment.
    Keywords: Aircraft Stability and Control
    Type: NASA-MEMO-12-1-58A
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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