Analysis of sonic boom measurements near shock wave extremities for flight near Mach 1.0 and for airplane accelerations

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National Aeronautics and Space Administration, 1974 - Science - 128 pages
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A method is developed to determine the flow field of a body of revolution in separated flow. The computer was used to integrate various solutions and solution properties of the sub-flow fields which made up the entire flow field without resorting to a finite difference solution to the complete Navier-Stokes equations. The technique entails the use of the unsteady cross flow analogy and a new solution to the two-dimensional unsteady separated flow problem based upon an unsteady, discrete-vorticity wake. Data for the forces and moments on aerodynamic bodies at low speeds and high angle of attack (outside the range of linear inviscid theories) such that the flow is substantially separated are produced which compare well with experimental data. In addition, three dimensional steady separated regions and wake vortex patterns are determined. The computer program developed to perform the numerical calculations is described.

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Contents

SUMMARY
1
ANALYSIS OF NEARSONIC FLIGHT TEST DATA
9
ANALYSIS OF SAFETY FACTOR DURING THRESHOLD MACH NUMBER FLIGHT
19

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