Midterm 1 - AOE 3104 Aircraft Performance Exam#1 Solutions...

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Unformatted text preview: AOE 3104 Aircraft Performance Exam #1 Solutions Problem 1. (30 points) An airfoil is being tested in a wind tunnel at standard sea level conditions. The free stream flow velocity is 160 ft/s. The pressure coefficient at a particular point on the airfoil is C p =- . 60. What is the flow speed at that point? If the wind tunnel speed is increased to 700 ft/s, what is the new pressure coefficient at the test point? What is the Mach number at the test point? Solution. Standard sea level conditions are ρ ∞ = 2 . 377 × 10 − 3 sl / ft 3 , T ∞ = 518 . 69 ◦ R , and P ∞ = 2116 . 2 lb / ft 3 . The speed of sound in standard sea level conditions is a = radicalbig γRT = radicalbig (1 . 4)(1716 . 488 ft lb / sl ◦ R)(518 . 69 ◦ R) = 1116 . 4 ft / s The free stream Mach numbers is therefore M ∞ = 160 ft / s 1116 . 4 ft / s = 0 . 143 < . 3 The flow may be treated as incompressible. Using Bernoulli’s equation for incompressible flow (and ignoring the small contribution from gravity), we have...
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Midterm 1 - AOE 3104 Aircraft Performance Exam#1 Solutions...

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