[領域] 空氣動力學 [來源] 課本習題 [題目] Consider a fighter with a thin supersonic airfoil in steady and level flight at Mach 3, the weight is 16,000 lbf and reference wing area is 196.1 sq ft to answer the following questions: (20%) 1. To calculate the lift coefficients at the altitude of 36,000 ft? 2. To calculate the angles of attack at the altitude of 36,000 ft? 3. To calculate the wave drag coefficients at the altitude of 36,000 ft? [瓶頸] 一些單位不知如何轉換@@ 請會幫幫忙 感謝^^ --

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