3.
2
=0.752>T*=EE831m
To y+1
p 2 Y/yl
_ = (_) = 0,488 -> p* =
V" = a* = Mr =
In a stationary straight cylinder with infinite length, a piston is moving with a constant
speed of 400m/S as shown in the figure. A normal shock wave will be generated in the
tu
6. An oblique shock generated at a compression corner with a deflection angle 9 = 15. A
straight horizontal wall is present above the corner, parallel to the free stream (see the
figure in example 3 of LEC 16). if the free stream M1 = 3.2, p1 = latm and T
5. When the Apollo command module returned to earth from the moon, it entered the
earths atmosphere at a Mach number of 36. Predict the air temperature at the
stagnation point of the Apollo module, assuming the free stream temperature to be
300K.
Given: M
4. Flow properties across an oblique shock wave can be determined using the normal shock wave
table provided the normal Mach numbers (Mm and an) were used. Why the column of % is
1
f 1702
not applicable for oblique shock waves? On the other hand, the colu
7. Pitot pressure measured in a supersonic air wind tunnel is 68.1 kPa (absolute). Before
the shock, T1 = 160 K and p1 = 11 kPa (absolute). Calculate the air speed in the wind
tunnel.
Given: p02 = 68.1 kPa, , T1 = 160 K and p1 = 11 kPa
Find: air speed
Sol
5. Consider a 10 half-angle wedge placed in a supersonic flow of Mach 3 at standard
conditions (10 = 101 kPa (abs), T = 288K) at an angle of attack of a =5. Determine
the angles of the shock waves and the surface pressure, temperature, total pressure and
T2 = 1.32 T1 = 365K, and V2 = = 537m/s
A supersonic air flow leaves a symmetric two-dimensional nozzle in parallel, horizontal flow
(region 1) with a Mach number of 2.6 and static pressure (in region 1) of 50 kPa. The nozzle
discharges to back pressure of
3
AB 439 Homework , assigned Mar. 2, due on Mar. 9 (before class)
1. Uniform airflow at Mach 3 passes into a concave comer of angle 15, as shown in the figure
below. The pressure and temperature in the supersonic flow are, respectively, 72kPa and 290K.
/
AB 439 Homework 4, assigned Sep. 16, due on Sep. 23 (10:30AM)
1. The maximum density in an isentropic compressible ow occurs at stagnation
condition. Evaluate the Mach number for air ow at which p0 and p differ by 2% and
5%. Comment on the significanc
From the shock wave table for M1 = 1.93, from the normal shock table-) 53 = 4.17 and
1
Ta = 1.63-) pl = 4.17 atm and T1 = 469.4 K
T1
A stagnation temperature is located on the nose of a supersonic aircraft cruising at
altitude of 12 km. Measured stagnatio