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Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetric diamond airfoil of semiangle epsilon = 15-degrees at an angle of attack to the free stream of 5-degrees when the upstream
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Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetric diamond airfoil of semiangle epsilon = 15-degrees at an angle of attack to the free stream of 5-degrees when the upstream Mach number and pressure are 2.0 and 2116 lb/ft2, respectively. The maximum thickness of the airfoil is t = 0.5 ft. Assume a unite length of 1 ft in the spanwise direction.

User Ofek Ron
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Answer:

Answers are given below. Detailed calculations are given in the attachment.

Step-by-step explanation:

Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetric-example-1
Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetric-example-2
User Laura Corssac
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