HWSol4 - 5.1. A two-dimensional or wedge-type diffuser...

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Unformatted text preview: 5.1. A two-dimensional or wedge-type 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: ode-Xasas xo.67><0.97 as: 0—8:]. FOI {3-8. 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 Mach-number of the flow is 0.3. Combustion in the burner (whose cross-sectional 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 one-dimensional 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+i-L‘Mi )M‘i ‘52 [It-ercl—Jg—fl‘ W 1 [is-Laos) ‘5) 0+1 tit-M4”); Solvma ifeVQtH/EIJ MLF = 070'? Post- _____ l+ 1"":— l+zi M: '32-! P62- l+XMl+ ‘+ if M22. ...
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HWSol4 - 5.1. A two-dimensional or wedge-type diffuser...

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