Question

A supersonic flow of air with Mach number of M₁=2.8 is deflected towards itself by 16^o. What is the Mach number M₂ behind the a weak oblique shock?

Answer 1

$\textup{Given data}\rightarrow$

M1 = 2.8

oblique shock angle 3 = 16"

Heat capacity ratio for air 1.4

Corner angle (0)

(MI* sin2 B) -1 M (3) * _ * () + 2 cos(23)) + 2 tan (θ) 2 * cot + 2 cos (2)

(2.82 sin2 (16) -1) 2.82 (1.42 cos (2 16)) +2 tan () 2 cot (16)*

)-6.1268

Mach number M2 behind the a weak oblique shock (M2

sin (β-8)

114 *2.82 sin2* (16) 1.4 * 2.82 * sir? * 16-14-1 M2 = sin (16-(-6. 1268))

$M_{2}=3.5276$

Mach number should be greater than 1 for weak or behind oblique wave

$\textup{Mach number should be less than 1 for after oblique wave}$