HW25solution - AAE 334 Fall 2011, Homework 25 SOLUTIONS Due...

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AAE 334 Fall 2011, Homework 25 SOLUTIONS Due Wednesday, November 16 at the beginning of class. 1. Compute manually (not using the PM_ Matlab functions) the pressure after a 10 degree expansion corner if the upstream flow is at Mach 2 and pressure of 100 kPa. 2. Compute manually (not using the PM_ Matlab functions) the temperature ratio, 1 2 / T T for the flow in the first question. 3. Using the PM_ Matlab functions compute the pressure on the upper surface of a flat plate airfoil at Mach 2 in units of upstream pressure. Plot the pressure on the upper surface and the lower surface pressure from HW 24 versus angle of attack. Besides explaining what you did and why, hand in a hard copy of the m-file and your plot. Part 1: (see Example 9.9 in the text too) From the Prandtl-Meyer table, we see that a Mach 2 flow has a Prandtl-Meyer angle of 26.38 o . Add on the ten degree turning angle and the new Prandtl-Meyer angle is 36.38 o . Nearest value to a Prandtl-Meyer angle of 36.38 o is M 2 =2.40
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This note was uploaded on 02/21/2012 for the course AAE 334 taught by Professor Collicott during the Fall '09 term at Purdue University-West Lafayette.

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HW25solution - AAE 334 Fall 2011, Homework 25 SOLUTIONS Due...

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