Abstract
Solutions for point and line sources are given, for the `transient ’ case only, in both stationary and moving co-ordinate systems. These are then integrated to give the solutions for a supersonic aerofoil (
a
) entering a sharp-edged gust, (
b
)following a sudden change of incidence. The method of obtaining oscillatory (flutter) solutions from (
b
) comes next, and it is Finally, the results of some calculations on the entry of supersonic aircraft into gusts are given. These results are in non-dimensional form and cover a fairly wide range of speeds, wing loadings and gust profiles. shown that these solutions check with those of Temple & Jahn (1945) and hence with others The failure of Collar’s simplified theory (Collar 1944) is also explained.
Reference6 articles.
1. Collar A. R. 1944 R.A.E. Rep. no. SME. 3278.
2. Garrick I. E. & Rubinow S. I. 1947 Amer. (containing a list o f'References). Avi. Com. Aero. Tech. Note no. 1383
3. Jeffreys H. 1946 Methods of mathematical physics Chap. 19. Cambridge University Press
4. von Karman T. H. & Sears W. R. 1938 J. A5 379.
5. Sohngen H. 1940 Luftfahrtforschimg 17 no. 11/12 (translated as R.T.P. Trans no. 1446).
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