An airfoil is tested inside a wind tunnel. The cross-section of the test section is rectangular as shown in the diagram below. A control volume is drawn around the rectangular cross-section. The top and bottom boundaries, 2 and 4, coincide with the upper and lower walls, while the other boundaries, 1 and 3, extend vertically between the walls. The flow is considered incompressible. Derive the expression for the drag force. U Po Ро x= -b/2 @ wall wall (3) x=b/2 Ty=h U-U. 1-0.5 cos 0.5 cos U₂=1.2U Pe=1.2225 p Pe y=-h 2h

An airfoil is tested inside a wind tunnel. The cross-section of the test section is rectangular as shown in the diagram below. A control volume is drawn around the rectangular cross-section. The top and bottom boundaries, 2 and 4, coincide with the upper and lower walls, while the other boundaries, 1 and 3, extend vertically between the walls. The flow is considered incompressible. Derive the expression for the drag force. U Po Ро x= -b/2 @ wall wall (3) x=b/2 Ty=h U-U. 1-0.5 cos 0.5 cos U₂=1.2U Pe=1.2225 p Pe y=-h 2h

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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