Consider a rectangular wing mounted in a low-speed subsonic wind tunnel. The wing model completely spans the test-section, so that the flow "sees" essentially an infinite wing. The wing has a NACA 23012 airfoil section and a chord of 0.23 m, where the lift on the entire wing is measured as 200 N by the wind tunnel force balance. Determine the angle of attack if the wing span, airflow pressure, temperature, and velocity are 2 m, 1 atm, 303 K, and 42 m/s, respectively. Refer to the Appendix graphs given below for standard values. (Round the final answer to the nearest whole number.)

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"Consider a rectangular wing mounted in a low-speed subsonic wind tunnel. The wing model completely spans the test-section, so that the flow "sees" essentially an infinite wing. The wing has a NACA 23012 airfoil section and a chord of 0.23 m, where the lift on the entire wing is measured as 200 N by the wind tunnel force balance. Determine the angle of attack if the wing span, airflow pressure, temperature, and velocity are 2 m, 1 atm, 303 K, and 42 m/s, respectively. Refer to the Appendix graphs given below for standard values" is in the attachment.

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