An aircraft has the CL-a curve shown in Figure 4.12. The following data applies: Weight = 20 000 lb Wing area, S = 340 sq. ft. Density altitude = 10 000 ft TAS = 242.4 kts. Find the aircraft's AOA for steady. CL 1.6- 1.4- 1.2- 1.0 0.8 0.6 0.4 0.2 0 L 02 ---Straight portion Clux J 1 4 6 8 10 12 14 16 18 Angle of attack (a) Eigure 4.12 C vs. AOA for a symmetrical airfoil. Stall angle of attack

An aircraft has the CL-a curve shown in Figure 4.12. The following data applies: Weight = 20 000 lb Wing area, S = 340 sq. ft. Density altitude = 10 000 ft TAS = 242.4 kts. Find the aircraft's AOA for steady. CL 1.6- 1.4- 1.2- 1.0 0.8 0.6 0.4 0.2 0 L 02 ---Straight portion Clux J 1 4 6 8 10 12 14 16 18 Angle of attack (a) Eigure 4.12 C vs. AOA for a symmetrical airfoil. Stall angle of attack

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 5.8P

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