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Unformatted text preview: 5.1. A twodimensional or wedgetype diffuser consists of two external oblique
shocks, a normal shock, and a subsonic internal section, as shown in the fig
ure. Assuming no external losses other than shock losses, and assuming the
subsonic section stagnation pressure loss is 3%, find the overall total pressure ratio at a flight Mach number of 2.5. Sketch the inlet shock system roughly to
scale and label all angles. M,=z.5 6=to° O‘=32.’ Mz=z.03 7° = 0,38 OI
M1=2.08 8=lo° o’ = 35" M3: {.66 Alli—3:: 0.985
M7, = 8: 0° M+=vaé5 %:‘§ = 0.872 Subsom'c diffusion fa ._. 0.97 P05: odeXasas xo.67><0.97 as: 0—8:].
FOI {38. A ramjet engine is to fly at a Mach number of 4 in an atmosphere whose tem
perature is 223 K. At entrance to the burner, the Machnumber of the flow is
0.3. Combustion in the burner (whose crosssectional area is constant) may
be represented approximately as heating of a perfect gas with constant 5pc
cific heat ratio. At the exit from the burner the temperature of the gas is
2462 K. Neglecting frictional effects in the burner and considering the flow
to be onedimensional throughout, estimate the Mach number of the gas leav ing the burner. Determine also the stagnation pressure loss due to heating
(i.e.. calculate the ratio of outlet and inlet stagnation pressures). E. (Ga:5) q 2. 1 2 7
13%: M$(I+LfMHr)l+JM1 9
73‘ £(t+r§_—’ 1") 1+ ertfj m MEOM’LLMf)“ n+iL‘Mi )M‘i ‘52 [Itercl—Jg—ﬂ‘ W 1 [isLaos) ‘5) 0+1 titM4”);
Solvma ifeVQtH/EIJ MLF = 070'?
Post _____ l+ 1"":— l+zi M: '32! P62 l+XMl+ ‘+ if M22. ...
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 Fall '08
 staff
 Fluid Dynamics, Mach number, Shock wave, stagnation pressure loss, perature, ure.

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