(c) Ackeret theory predicts (prove this in the next question) that drag is minimized if the airfoil is symmetric (i.e., if p = 0.5). If you are NOT finding any differences, then you are not exercising hard enough! If you find any differences in your outcome compared to linear theory, try to explain them. m for various choices of the other parameters, viz. Ideally, you should create several plots of ci/cd vs.
#Double wedge airfoil code
See if shock-expansion theory leads to the same conclusions by systematically exercising your code for various choices of the five input parameters. (b) Ackeret theory predicts that lift is independent of camber, and wave drag increases with camber, so that (wave) drag-to-lift ratio increases with camber. If you want, you can also calculate and return the sectional pitching moment (for no extra credit!). The outputs from the code should be (i) sectional lift coefficient, and (ii) sectional wave drag coefficient. The inputs to the code should be (a) t, (b) m, (c) p, (d) a, and (e) Moo. (a) Write a Python code to calculate the flow over this airfoil, using shock-expansion theory.
![double wedge airfoil double wedge airfoil](https://ars.els-cdn.com/content/image/3-s2.0-B9780081001943000080-gr022.jpg)
Note that in the textbook problem, p is restricted to be 0.5 we allow it to be a variable. For reference, see Example Problem 7.5 of Houghton et al. It faces a supersonic freestream of Mach number Moo at an angle of attack a. The maximum thickness and camber (if any both occur at p times the chord from the leading edge. It has chord length of c, fractional maximum thickness t, and fractional maximum camber m.
![double wedge airfoil double wedge airfoil](https://image1.slideserve.com/2759643/wing-section1-n.jpg)
![double wedge airfoil double wedge airfoil](https://ars.els-cdn.com/content/image/3-s2.0-B9780080966328000072-e07-05-9780080966328.jpg)
Consider the asymmetric cambered double-wedge airfoil shown below.