1.

What is the ratio of throat area of diffuser to nozzle in supersonic wind tunnel with flow at Mach 2.7?(a) 0.4236(b) 0.8338(c) 2.36(d) 1.199I have been asked this question in class test.My question is taken from Supersonic Wind Tunnels topic in chapter Compressible Flow through Nozzles, Diffusers and Wind Tunnels of Aerodynamics

Answer»

Right choice is (c) 2.36

To explain: Given M = 2.7

If we assume that there’s a normal SHOCK PRESENT at the entrance of the diffuser, then using the GAS table we can find the ratio of total pressures \(\frac {p_{01}}{p_{02}}\).

For M = 2.7, \(\frac {p_{02}}{p_{01}}\) = 0.4236

Using the relation beween the throat areas and total pressure we get

\(\frac {A_{t2}}{A_{T1}} = \frac {p_{01}}{p_{02}} = \frac {1}{0.4236}\) = 2.36


Discussion

No Comment Found

Related InterviewSolutions