This document is posted to help you gain knowledge. Please leave a comment to let me know what you think about it! Share it to your friends and learn new things together.
Transcript
Gustavo Narez MAE 3306-‐001 Dr. Chudoba Jan. 27, 2012 Problem 1 An airfoil has section lift, drag, and quarter-‐chord moment coefficients
where 𝛼 is the angle of attack in the radians. Find the center of pressure and the aerodynamic center of the airfoil for angles of attack of -‐5, 0, 5 and 10 degrees.
Gustavo Narez MAE 3306-‐001 Dr. Chudoba Jan. 27, 2012 Problem 2 Compute the absolute temperature, pressure, density, and speed of sound for the standard atmosphere defined in table 1.2.1 at a geometric altitude of 35,000 meters. Solution
Gustavo Narez MAE 3306-‐001 Dr. Chudoba Jan. 27, 2012 Problem 3 Compute the absolute temperature, pressure, density, and speed of sound, in English units, for the standard atmosphere that is defined in table 1.2.1 at a geometric altitude of 95,000 ft. Solution 𝐻 = 95,000 𝑓𝑡 . 3048