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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 1983, Vol. 4 ›› Issue (4): 101-104.
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Bi Shiguan
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Abstract: The theoretical specific impulse formula for two-phase flow in nozzle of rocket-ramjet engine is derived on the basis of similarity to that used for rocket engine.Theoretically,it is proved that for both these engines,the properties of two-phase flow in nozzle can be analysed with a common combined parameter which is equivalent to exhaust velocity.A simple estimation method for specific impulse losses of two-phase flow with variable lag is provided.An approximate solution dealing with the singularity is proposed.
Bi Shiguan. THEORETICAL SPECIFIC IMPULSE FOR TWO-PHASE FLOW IN NOZZLE OF ROCKET-RAMJET ENGINE——A SIMPLE ESTIMATION METHOD[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1983, 4(4): 101-104.
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