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Steady and unsteady terminal shock aerodynamics on cone cylinder bodies

机译：锥筒体上的稳定和不稳定的终端冲击空气动力学

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Effects of shock induced boundary layer separation on cone cylinder body aerodynamics

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作者
Ericsson, L. E.;
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年度 1967
页码 1-81
总页数 81
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
AERODYNAMIC CHARACTERISTICS; BOUNDARY LAYER SEPARATION; CONICAL BODIES; CYLINDRICAL BODIES; SHOCK WAVES; UNSTEADY AERODYNAMICS; ANGLE OF ATTACK; ELASTODYNAMICS; SUBSONIC FLOW; SUPERSONIC FLOW;

机译：空气动力学特征;边界层分离;圆锥体;圆柱体;冲击波; UNsTEaDY aERODYNamICs;攻击角度;弹性力学; sUBsONIC FLOW;超音速流;

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Steady and unsteady terminal shock aerodynamics on cone cylinder bodies

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