Accession Number:

ADA280146

Title:

A Comparison of the Experimental Subsonic Pressure Distributions about Several Bodies of Revolution with Pressure Distributions Computed by Means of the Linearized Theory

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CENTER

Personal Author(s):

• Matthews, Clarence W.

Report Date:

1953-01-01

Pagination or Media Count:

32.0

Abstract:

An analysis is made of the effects of compressibility on the pressure coefficients about several bodies of revolution by comparing experimentally determined pressure coefficients with corresponding pressure coefficients calculated by the use of the linearized equations of compressible flow. The results show that the theoretical methods predict the subsonic pressure- coefficient changes over the central part of the body but do not predict the pressure-coefficient changes near the nose. Extrapolation of the linearized subsonic theory into the mixed subsonic-supersonic flow region fails to predict a rearward movement of the negative pressure-coefficient peak which occurs after the critical stream Mach number has been attained. Two equations developed from a consideration of the subsonic compressible flow about a prolate spheroid are shown to predict, approximately, the change with Mach number of the subsonic pressure coefficients for regular bodies of revolution of fineness ratio 6 or greater.

Descriptors:

• *SUBSONIC FLOW
• *PRESSURE DISTRIBUTION
• SURFACE ANALYSIS
• COMPARISON
• ANGLE OF ATTACK
• PRANDTL NUMBER
• BODIES OF REVOLUTION
• FREE STREAM
• COMPRESSIBLE FLOW
• MACH NUMBER

Subject Categories:

• Aerodynamics
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE