By Brian J. Cantwell
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Sample text
A normal shock stands in front of the inlet. 5 3 P0 4 e M0 = 3 shock and the stagnation temperature at station 4 is T t4 = 2000K . 5 = 8 , A 1 = A 3 = A 4 and A 4 ⁄ A e = 3 . Determine the dimensionless thrust T ⁄ ( P 0 A 1 ) . Do not assume f<<1. Neglect stagnation pressure losses due to wall friction and burner drag. Assume that the static pressure outside the nozzle has recovered to the ambient value. 5 = A 3 . By what proportion would the air mass flow change? Solution - The first point to recognize is that the stagnation pressure at station 4 exceeds the ambient by more than a factor of two - note the pressure outside the nozzle is assumed to have recovered to the ambient value.
The ramjet is clearly best suited for high Mach number flight and the optimum Mach number increases as the maximum engine temperature increases. The specific impulse of the ideal ramjet is 1⁄2 2 ----------- ( τ r – 1 ) I sp g γ – 1 τ f – τr τλ ---------- = ----------------------------------------------- ------------------ ----- – 1 τλ – τr a0 τ f – τλ τr -----------------τ f – τλ . 43) The specific impulse also has an optimum but it is much more gentle than the thrust optimum as shown below.
The ramjet is clearly best suited for high Mach number flight and the optimum Mach number increases as the maximum engine temperature increases. The specific impulse of the ideal ramjet is 1⁄2 2 ----------- ( τ r – 1 ) I sp g γ – 1 τ f – τr τλ ---------- = ----------------------------------------------- ------------------ ----- – 1 τλ – τr a0 τ f – τλ τr -----------------τ f – τλ . 43) The specific impulse also has an optimum but it is much more gentle than the thrust optimum as shown below.