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A General Method (depending on the Aid of a Digital Computer) for Deriving the Structural Influence Coefficients of Aeroplane Wings
A. B. Haines
B. D. Henshall
Colin Sinnott
D. W. Bryer
David Williams
Dietrich Küchemann
E. Downham
E. L. Goldsmith
E. W. E. Rogers
F. A. MacMillan
G. L. Shires
I. T. Minhinnick
Ian H. Rettie
J. H. Horlock
J. Weber
John H. Argyris
K. C. Wight
K. W. Newby
Leslie Colin Woods
P. F. Jordan
R. B. Payne
R. J. Monaghan
S. F. J. Butler
C. F. Griggs
C. J. Berry
C. W. Rhodes
D. E. Walshe
G. E. Munns
Sydney Kelsey
Henry Clifford Garner
其他書名
Parts I and II
出版
H.M. Stationery Office
, 1958
URL
http://books.google.com.hk/books?id=BxDRzgEACAAJ&hl=&source=gbs_api
註釋
The velocity distribution around the nose of a NACA 0015-64 aerofoil was found by experiment and that around the nose of a Piercy 15/40 aerofoil by calculation for various angles of incidence and flap deflection. It was established that at all incidences this velocity distribution is a function of the position of the stagnation point, irrespective of the flap deflection. This result is show to be true generally, and it is suggested that use might be made of it in the design of a lift-coefficient meter, which could also be used to give warning of a stall.--Author's summary.