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Effect of Wall Divergence on Sonic Flows in Solid Wall Tunnels

Published online by Cambridge University Press:  04 July 2016

D. Tirumalesa  and
B. Satyanarayana
D. Tirumalesa
Affiliation:
National Aeronautical Laboratory, Bangalore
B. Satyanarayana
Affiliation:
National Aeronautical Laboratory, Bangalore
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Extract

The effect of wall divergence (in excess of the normal value given for compensating the Boundary Layer growth on the tunnel walls), on the simulation of Sonic flows in solid wall wind tunnels is presented in this note which is a condensed version of Ref. 1.

Recently Spreiter showed that flows with free stream Mach number one can be simulated reasonably well in choked solid tunnels. Berndt and Petersohn showed that the thickening of the boundary layer on the walls of solid wall tunnels reduced the interference considerably. Wall divergence θg in excess of the normal one of about one degree (used for Boundary Layer compensation) may lead to favourable conditions for the thickening of the Boundary Layer and this appeared to be an interesting way of reducing the interference.

Type
Research Article
Information
The Aeronautical Journal , Volume 66 , Issue 614 , February 1962 , pp. 125 - 128
Copyright
Copyright © Royal Aeronautical Society 1962

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References

1. Tirumalesa, D., Satyanarayana, B. Simulation of Sonic Flows in Choked Wind Tunnels. Aero Eng. Dept., Ind. Inst, of Sc, HSAL Report, No. 69, Bangalore.Google Scholar
2. Spreiter, J. R., Smith, D. W., Hyett, B. J. (1960). A Study of Simulation of Flow with Free Stream Mach Number One in a Choked Wind Tunnel. NASA T.R. R-73 (1960).Google Scholar
3. Berndt, S. B. (1957). On the Influence of Wall Boundary Layers in Closed Transonic Test Section. FFA Rep. 71 Stockholm, 1957.Google Scholar
4. Petersohn, E. G. M. (1952). Some Experimental Investigations on the Influence of Wall Boundary Layers Upon Wind Tunnel Measurements at High Subsonic Speeds. FFA N.R. 44, Stockholm, 1952.Google Scholar
5. Spreiter, J. R., Alksne, A. Y. (1958). Thin Airfoil Theory Based on Approximate Solution of the Transonic Flow Equation. NACA Rep. 1359, 1958.Google Scholar