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Reynolds Number Extrapolation of Transonic Wing Pressure Data Affected by Shock-Induced Separation
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Abstract
A method is discussed which accounts for the effect of changes in Reynolds number on the pressure distributions of transonic wings. The major Reynolds number effect is a change in shock location which accompanies a change in trailing-edge separation. The method discussed here depends on several characteristics of separating transonic flows, each of which is supported by experimental data from a variety of transonic wing tests: (1) Pressure distributions forward of the shock are not affected by trailing-edge separation. (2) When trailing-edge separation occurs, the shock moves forward. The relationship between shock location and trailing-edge pressure is the same whether changes are caused by changes in Reynolds number, changes in transition location or use of separation control devices (BLC, vortex generators, etc.). (3) The combined effects of changes in angle of attack and Mach number on trailing-edge separation are shown to be a function solely of the transonic similarity parameter previously presented by Melnick and Grossman. (4) When correlated in terms of the M-G similarity parameter, the trailing-edge separation data are shown to follow a simple and universal variation with Reynolds number.
The method discussed here applies to cases where there is no separation at the shock and scale effects are dominated by conditions at the trailing edge. Additional study is required for those cases where separations exist at both the shock and the trailing edge.
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Citation
Cahill, J., "Reynolds Number Extrapolation of Transonic Wing Pressure Data Affected by Shock-Induced Separation," SAE Technical Paper 861846, 1986, https://doi.org/10.4271/861846.Also In
References
- Haines A.B. Holder D.W. Pearcey H.H. “Scale Effects at High Subsonic and Transonic Speeds, and Methods for Fixing Boundary Layer Transition in Model Experiments,” R&M No. 3012 Aeronautical Research Council
- Pearcey H.H. Osborne J. Haines A.B. “The Interaction Between Local Effects at the Shock and Rear Separation - A Source of Significant Scale Effects in Wind Tunnel Tests on Airfoils and Wings,” AGARD C.P. 35 Transonic Aerodynamics September 1968
- AGARD C.P. 83 “Facilities and Techniques for Aerodynamic Testing at Transonic Speeds and High Reynolds Number,” April 1971
- Cahill J.F. Connor P.C. “Correlation of Data Related to Shock-Induced Trailing-Edge Separation and Extrapolation to Flight Reynolds Number,” NASA Contractor Report 3178 September 1979
- Khan M.M.S. Cahill J.F. “New Considerations on Scale Extrapolataion of Wing Pressure Distributions Affected by Transonic Shock-Induced Separation,” NASA Contractor Report 166426 October 1984
- Melnik R.E. Grossman B. “Analysis of the Interaction of a Weak Normal Shock Wave With a Turbulent Boundary Layer,” AIAA Paper No. 74-598 June 1971