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The role of wind tunnels in future aircraft development

Published online by Cambridge University Press:  04 July 2016

Ronald Smelt
Ronald Smelt*
Affiliation:
Lockheed Corporation
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Extract

Presentation of the Daniel and Florence Guggenheim International Memorial Lecture is both a high honour and a challenge. The challenge is implicit in the final two words—to present to you both a lecture and a fitting memorial to the remarkable Guggenheim family. I believe that the subject which I have chosen is particularly appropriate for this task. As many of you know, Daniel Guggenheim, in the years from 1925 to his death in 1930, sponsored and endowed the now famous Guggenheim Aeronautical Laboratories in major universities across the USA. It is clear from his writing that these were not simply gifts to the universities—conventional endowments—but that they reflected Daniel Guggenheim's vision of a future in which the aircraft would link cities and countries in a safe, efficient civil transport system surpassing all other modes of travel.

Type
Research Article
Information
The Aeronautical Journal , Volume 82 , Issue 815 , November 1978 , pp. 467 - 474
Copyright
Copyright © Royal Aeronautical Society 1978 

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References

1. Reshotko, E. Drag reduction by cooling in hydrogen fuelled aircraft. Eleventh ICAS Congress, Lisbon, September 1978.Google Scholar
2. Blackwell, J. A. Scale effects on advanced aircraft wing designs. Proceedings of Lockheed-Georgia Viscous Flow Symposium, June 1976.Google Scholar
3. Chapman, D. R., Mark, H. and Pirtle, M. W. Computers vs wind tunnels for aerodynamic flow simulations. Astronautics and Aeronautics, April 1975.Google Scholar
4. Smelt, R. Power economy in high-speed wind tunnels by choice of working fluid and temperature. Royal Aircraft Establishment Report No Aero 2081, August 1945.Google Scholar
5. Mack, L. M. Boundary layer stability theory. Jet Propulsion Laboratory, Pasadena, Report No 900-277, 1969.Google Scholar
6. Reshotko, E. Stability theory as a guide to evaluation of transition data. AIAA Journal, Vol 7, p 1086, 1969.Google Scholar
7. Kendall, J. M. JPL experimental investigations. In Proc of Boundary Layer Transition Workshop, Aerospace Report TOR 0172, Vol IV, 2-1.Google Scholar
8. Potter, J. L. The unit Reynolds number effect on boundary layer transition. Doctoral Dissertation, Vander- bilt University, Tennessee, May 1974.Google Scholar
9. Blackwell, J. A. Preliminary study of effects of Reynolds number and boundary layer transition location on shock-induced separation. NASA Tech Note TN D-5003, January 1969.Google Scholar
10. Spreiter, J. R. and Stahara, S. S. Developments in transonic steady and unsteady flow theory. Paper No 76-06, Tenth ICAS Congress, Ottawa, October 1976.Google Scholar
11. Future computer requirements for computational aerodynamics. Proceedings of a Workshop held at Ames Research Center. NASA Conference Publication 2032, February 1978.Google Scholar
12. Case, K. M., et al. Numerical simulation of turbulence. Stanford Research Institute Technical Report JSR-73-3, 1973.Google Scholar