A supersonic flow of air has a pressure of \(1 \times 10^{5} \mathrm{~N} / \mathrm{m}^{2}\) and a temperature of \(350 \mathrm{~K}\). After expanding through a \(35^{\circ}\) turn, the Mach number is 3.5.

(a) What are the final temperature and pressure?

(b) Make a sketch similar to Figure P8.2 and determine angles \(\theta_{1}, \theta_{2}\), and \(\theta_{3}\).

Transcribed Image Text:

M 0 = 142.7 6-19.2 M Figure P8.2