Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness: Sinusoidal variation, Part 2
Maurice Holt · Bohyun Yim
Jan 1960 · United States Air Force, Office of Scientific Research
Ebook
70
Pages
About this ebook
In this case the whole disturbed flow field also varies sinusoidally with span. In region (i) the pressure satisfies the telegraph equation and the problem of calculating the disturbed flow field reduces to an integro-differential-difference equation for the distorted shock shape function. The solution of this equation, the existence and uniqueness of which is established, is obtained in the form of series expansions in chordwise distance on the shock ... In region (ii) the surface pressure satisfies a Volterra integral equation which can be solved by a simple numerical procedure. The present paper takes no account of edge effects, which must be treated separately as a conefield problem.
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