Abstract
One of the fundamental problems preventing commercial transport from going supersonic is the creation of Sonic Boom due to strong shock waves. Although it is nearly impossible to sufficiently reduce the shock waves generated by the aircraft designed conventionally to meet acceptable Sonic Boom levels at ground, it has been shown by the present authors that Sonic Boom can be reduced by using biplane. Here, the Busemann biplane is used as the basic shape of biplane configuration. Even though the Busemann biplane has a wide range of low wave drag, it has a choked flow phenomenon at off-design condition. Hence, we study methods for avoiding choked flow phenomenon for biplane by changing wing configuration. It was found that the configuration used in this research can alleviate the problem of sudden increase of the C_d value in choked flow phenomenon.
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