Consider a rectangular wing with NACA O009 airfoil section spanning the test section of a wind tunnel, the test section airflow conditions are standard sea level w/a velocity of 116 mi/hr. The wing is at an angle attack of 4° and the wind tunnel force balance measures a lift of 28.43 lbf. What is the area of the wing? R.N = 3.0 X106; C̟ at angle attack of 4° = 0.4

Consider a rectangular wing with NACA O009 airfoil section spanning the test section of a wind tunnel, the test section airflow conditions are standard sea level w/a velocity of 116 mi/hr. The wing is at an angle attack of 4° and the wind tunnel force balance measures a lift of 28.43 lbf. What is the area of the wing? R.N = 3.0 X106; C̟ at angle attack of 4° = 0.4

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.29P: Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance...

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Consider a rectangular wing with a NACA 0009 airfoil section spanning the test section of a wind tunnel. The test-section airflow conditions are standard sea level with a velocity of 120 mi/h. The wing is at an angle of attack of 4° and Cl is 0.4, and the wind tunnel force balance measures a lift of 29.5 lb. What is the area of the wing?
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