A student is testing a wing in a subsonic wind tunnel. The inlet has a cross-sec
ID: 1819868 • Letter: A
Question
A student is testing a wing in a subsonic wind tunnel. The inlet has a cross-sectional area of 6 nr with air at T = 290 K, rho = 99.0 kPa. The cross-sectional area of the test section is 1.5 m2. A pitot-static tube placed at the entrance of the test section and connected to a water (p - 1000 kg/m3) manometer indicates Ah = 18.5 cm. What is the velocity in the test section? What is the inlet velocity and what is the stagnation pressure at the inlet? A static pressure tap on the suction surface at the thickest point on the airfoil measures a pressure of 95.6 kPa. What is the velocity and the pressure coefficient at that point on the wing? If the velocity were increased such that the lift on the wing doubled, would you expect this pressure coefficient to increase or decrease? The rectangular, symmetrical wing has a chord of 10 cm and a wings pan of 30 cm. At an angle of attack of 5 degree s, the wind tunnel balance measures a lift of 16.8 N and a drag of 3.5 N. What are the lift and drag coefficients for this wing? The student replaces the original wing with one that is identical except it has a wingspan of 60 cm. What is the expected lift for this wing assuming the same test conditions as before?Explanation / Answer
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