Homework #1: 7.4, 7.8, 7.9, 7.10, 8.2
Homework #2: 8.3, 8.5, Additionally, write computer program to replace table A: In particular
Homework #3: 8.7, 8.8, 8.16, 8.17
Homework #4: 9.1, 9.2: also find the value of the turning angle, theta, 9.3
Homework #5: Probs 9.7, 9.8, 9.9 And, write a program to solve eq. 9.23:
Homework #6: Probs 9.10, 9.11, 9.13, 9.15 and
Homework #7:
9.16
Homework #8: probs 10.3, 10.4, 10.7, 10.8; but first 10.additional: Add A/A* to your isentropic flow program: That is, add the option for the user to specify A/A*. Use Newton’s method to find both the supersonic and the subsonic Mach number. Print out all elements of a row in appendix A, for both Mach numbers. Provide sample output for A/A*=2 and 5.
Homework #9: 10.9. In this problem regard the stated pressures to be P_a. Add e) P_a=0.4atm f) P_a=0.1atm; 10.10; 10.12 (note that `sea level conditions' mean P=1atm and T=288K inside the test section.)
Homework #10:
10.13 and
A converging-diverging nozzle diverges linearly after the throat:
for x> 0.
If A_exit=4A_throat and P_ambient=0.5P_0 what is
the sonic area after the shock, i.e., A*_2/A_throat?
What are the Mach numbers on either side of the shock?
What is the position, x_s/x_exit, of the shock?
(Use the formulas derived in class, or your method of solution to 10.9.c.)
Homework #11: 11.3, 11.4, 11.7
Homework #12: 12.1, 12.3; but do not compare to 9.14. The problem should cite fig. 9.36
Final exam May 3 9:45-11:45 a.m. Print Formula Sheet and bring it.