The Effect of Atmospheric Nonuniformity On Sonic Boom Intensities
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概要
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A theoretical investigation is presented on the effect of atmospheric nonuniformity on the decay of shock waves generated by a supersonic aircraft in steady level flight with special reference to sonic boom problem. At the outset, analysis is made for an axisymmetric body in an adiabatic atmosphere, together with two-dimensional body case for the sake of reference. The decay rule of a bow shock due to atmospheric nonuniformity is obtained by the application of Whitham's theory on the behavior of shock waves at large distances from the body in a uniform medium to the case of a stratified atmosphere. Numerical calculations are carried out at flight Mach numbers from 1.3 to 3.0 and flight altitudes up to 10km. Extension of the above-mentioned technique makes it possible to obtain the decay of a bow shock in an arbitrary stratified atmosphere and a numerical calculation is made for the case of an axisymmetric body in a standard atmosphere at the same flight Mach numbers as above and flight altitudes up to 20km. The result shows good agreement with existing flight test-data and other theoretical result by different method.
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