Question

3 M = 2.2 M, = 22 124 12 (a) (b) Figure 4.55 (a) One-shock spike, (b) two-shock spike diffuser. Figure 4.56 Supersonic flow past a sharp corner. M OM P12 м. 10° Figure 4.57 Flow through incident and reflected oblique shocks. M = 2.4 P1 = 101 kPa 10° Oblique Shock and Expansion Waves 219 Figure 4.58 Oblique shock reflection from a solid wall. M,=2.2 Po= 100 kPa M2 M 30° Air X Jet boundary Figure 4.59 Overexpanded jet issuing from a nozzle.

GAS DYNAMICS

Answer 1

(4.36) do LLLLLLLLL llo LACULUIius M3 My=2.4 Leu 10. P1 - 101 kpl 1 3 2 Biz 130=10 from, obleque Shock table A-3, (weak qolution) @M2 = 24, 0 = 10 + R2 = 33.02° dena, 855 M2 = Man = M2.SPn B = . (2.4) Sin (35.02) - 1.308 from Normal shock table, @ Man1.63078 → Man = 0.7809 Min ~ 1.31 P2 1.8354 P1 Therefore, 0.7809 - 1.99 Sin (33-02-10) Now, for M2 = 1.99 ; and 0 = 18, from Oblique Shock table, B23 = 39.3.1° Men = Ma. Sin ( Pes) - 1.996 x sin (3 9.3.10) M20 = 1.265 & for, Man= 1.265; normal shock tasle gires, Man = 0.8016 Man Sen (3-0) P2 Pq = 1.7150 Hence, 0.8016 NI co 1.637 1.64 Any Sen (39.31-10) Thes P3 P3, P2 Pa Pl = (1.7150)*(1.8354) = 3.147711 Pa → P3 (3.14771 X 101 kpa) [P3 P3 = 317.91 Rpa Any