HW23 - Mach number 2 Add the curve through the maximum turning angles as a dashed line 3 20 extra credit add the curve separating subsonic

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AAE 334 Fall 2011, Homework 23 Due Monday, November 7 at the beginning of class. The oblique shock chart in the test is difficult to read at times. You can create your own quite simply with use of the Matlab routines supplied on Blackboard this semester. For this assignment, 1. create an oblique shock chart for Mach numbers of 1.25 to 2.75 in steps of 0.25. There is an easy way and a long way to do this. To do it the easy way, for each Mach number, create a vector of wave angles ranging from the minimum possible wave angle for that Mach number up to the maximum possible wave angle for that Mach number. Then compute the turning angle for every wave angle at that Mach number. Then plot wave angle in degrees versus turning angle in degrees. Use about 200 points per Mach number for your final plot once you have your code working with about 20 points per
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Unformatted text preview: Mach number. 2. Add the curve through the maximum turning angles as a dashed line. 3. 20% extra credit : add the curve separating subsonic downstream flow from supersonic downstream flow as a solid line. 4. A second useful chart for aerodynamic design, which is not included in your text, is constant Mach number curves showing 1 2 / p p versus turning angle in degrees. Create this chart too. Hand in hard copy of your generously-commented m-file or m-files and hard copies of your appropriately labeled, neat, and legible plots. Also describe how you performed part 3 if you did so. Just list the Mach numbers in the title of the plot, don’t waste time trying to label each curve in the plot (then ponder this: if given an unlabeled oblique shock chart, how could you identify what upstream Mach numbers are plotted?)...
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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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