Supersonic Flow Past Pointed Bodies of Revolution at Small Angles of Attack

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概要

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• A general method of theoretical approach to supersonic flow past lifting bodies of revolution with arbitrary geometry is presented assuming that the flow behind an attached shock wave consists of a basic non-lifting field upon which is superimposed a perturbation field due to small angles of attack and is particularly applied to circularcones as a simple example. It is shown that, although the nonlinearity in fundamental equations predicting the basic field has a predominant effect on aerodynamic characteristics of the body, a linear approximation of perturbation field with respect to angle of attack still seems to be available even if the body is not so slender. Experimental results also confirm this.

• 宇宙航空研究開発機構の論文

著者

• IWASAKI Kenjiro

  Mechanical Engineering Research Laboratory, Hitachi Ltd.

関連論文

• Supersonic Flow Past Pointed Bodies of Revolution at Small Angles of Attack

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