Accession Number:

AD0801757

Title:

SUPERSONIC FLOW WITH VORTICITY ABOUT A SLIGHTLY YAWING BODY OF REVOLUTION,

Descriptive Note:

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s):

Report Date:

1952-01-01

Pagination or Media Count:

71.0

Abstract:

Steady inviscid flow about a slightly yawing body of revolution has been approximated by a perturbation of the axisymmetric flow about the same body at the same free stream Mach Number. It is generally but not always assumed that the products of the perturbations are negligible. The hyperbolic system of partial differential equations of motion is transformed into characteristic form, then the perturbations are expanded in Fourier series, most of whose terms are shown to vanish. The remaining perturbation coefficients satisfy a linear homogeneous system of partial differential equations. The procedure has been developed with sufficient generality to include vorticity, and is applicable to bodies whose meridian sections have discontinuous slopes. Pressure ratios, normal force coefficients, and center of pressure positions calculated by this method for a 10 degree semi-angle cone cylinder with free stream Mach Number of 1.72 are in good agreement with wind tunnel and free flight data for yaws not exceeding five degrees. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE