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Static-pressure probes that are theoretically insensitive to pitch, yaw and Mach number

Published online by Cambridge University Press:  29 March 2006

A. M. O. Smith  and
A. B. Bauer
A. M. O. Smith
Affiliation:
McDonnell Douglas Corp., Douglas Aircraft Co., Long Beach, California
A. B. Bauer
Affiliation:
McDonnell Douglas Corp., Douglas Aircraft Co., Long Beach, California
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Abstract

The idea of distributing static probe cross-sectional areas so as to render the probe insensitive to Mach number is combined here with that of using non-circular cross-sections to render probes insensitive to yaw and angle of attack. Appropriate non-circular cross-sections are described in detail, and a general means of designing blunt or slender probes to have zero sensitivity to yaw and angle of attack in potential flow is described. Four experimental probes have been tested, and test results are presented. These results show that the probes are quite insensitive to yaw and angle of attack within certain limiting angles, which are assumed to correspond to the onset of flow separation.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 44 , Issue 3 , 26 November 1970 , pp. 513 - 528
Copyright
© 1970 Cambridge University Press

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References

Bauer, A. B. 1969 Supersonic test results for Douglas static probe no. IX. McDonnell Douglas Rep. no. DAC 67982.Google Scholar
Hess, J. L. & Smith, A. M. O. 1966 Calculation of potential flow about arbitrary bodies. Progress in Aeronautical Sciences, 8. Pergamon.
Hess, J. L. & Smith, A. M. O. 1967 Static-pressure probes derived from supersonic slender-body theory. J. Aircraft, 4, 409–415.Google Scholar
Smith, A. M. O. & Brumby, R. E. 1968 A static pressure probe that is theoretically insensitive to pitch, yaw and Mach number. McDonnell Douglas Rep. no. DAC 66624.Google Scholar