The purpose of this work is the determination of the two-dimensional flow past an airfoil placed in a stream of inviscid fluid, uniform to the infinity, under the following conditions:na) The stream at infinity, referred to a system of axes (x*,y*), has a speed U∞ and a Mach number M∞ < 1 which is sufficiently high so that a supersonic region exists:nb) the symmetrical airfoil starting from a given instant, which will be conventionally considered as initial, has a translatory motion [re¬ferred to the same system (x*,y*)] in the-direction of its symmetry axis.
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