ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • Aircraft Stability and Control  (2)
  • Fluid Mechanics and Thermodynamics; Aerodynamics  (1)
Collection
Keywords
Years
  • 1
    facet.materialart.
    Unknown
    Predicted Gas Properties in the Shock Layer Ahead of Capsule-Type Vehicles at Angles of Attack (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A method for determining shock-wave shapes, stagnation-point location, and flow-field properties for spherically blunt bodies at angle of attack was developed. The method is applicable to perfect gas flows and equilibrium flow of real gases. The results given by the method for shock surface and stagnation-point location are compared with experimental values. Comparison of the shock-layer density and temperature distribution are also made between the results of the method and those of a more exact procedure for a sphere. These comparisons indicate satisfactory agreement.
    Keywords: Fluid Mechanics and Thermodynamics; Aerodynamics
    Type: NASA-TN-D-1423 , A-596
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    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
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...