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Consider a rectangular wing mounted in a wind tunnel. The wing model completely spans the test section so that the flow sees essentially an infinite wing. The wing has a NACA 2421 airfoil section, a chord of 3.0 m, and a span of 20 m. The tunnel is operated at the following test conditions: P = 101,000 N/m2; T = 35° C; V = 50 m/s; and µ = 1.9 * 10 -5 kg/(m s). (a) Determine the operating Reynolds number. (b) Calculate the lift, drag, and moment about the aerodynamic center for an angle of attack of 8 deg andRe=9*106 (c) At a Reynolds number of 3 * 106, find the following: 1) What is the stalling angle of attack for this airfoil? 2) What is the angle of attack for zero lift? 3) What is the lift-curve slope?

Consider a rectangular wing mounted in a wind tunnel. The wing model completely spans the test section so that the flow sees essentially an infinite wing. The wing has a NACA 2421 airfoil section, a chord of 3.0 m, and a span of 20 m. The tunnel is operated at the following test conditions: P = 101,000 N/m2; T = 35° C; V = 50 m/s; and µ = 1.9 * 10 -5 kg/(m s). (a) Determine the operating Reynolds number. (b) Calculate the lift, drag, and moment about the aerodynamic center for an angle of attack of 8 deg andRe=9*106 (c) At a Reynolds number of 3 * 106, find the following: 1) What is the stalling angle of attack for this airfoil? 2) What is the angle of attack for zero lift? 3) What is the lift-curve slope?

Elements Of Electromagnetics
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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Consider a rectangular wing mounted in a wind tunnel. The wing model completely spans the test
section so that the flow sees essentially an infinite wing. The wing has a NACA 2421 airfoil section,
a chord of 3.0 m, and a span of 20 m. The tunnel is operated at the following test conditions: P =
101,000 N/m2; T = 35° C; V = 50 m/s; and µ = 1.9 * 10 -5 kg/(m s).
(a) Determine the operating Reynolds number.
(b) Calculate the lift, drag, and moment about the aerodynamic center for an angle of attack of 8 deg andRe=9*106
(c) At a Reynolds number of 3 * 106, find the following:
1) What is the stalling angle of attack for this airfoil?
2) What is the angle of attack for zero lift?
3) What is the lift-curve slope?

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