A ramjet burner is being designed for an overall stagnation temperature ratio of 4 and outlet Mach number of 0.85. Two possibilities are being considered:
a.The burner cross-sectional area is to be constant.
b.The burner cross-sectional area is to be varied in the stream direction in such a way as to maintain the Mach number uniform within the burner. As a first approximation, assume the static pressure varies linearly with duct cross-sectional area.
For both cases determine the ratio of outlet and inlet stagnation pressures. For the second case determine the ratio of outlet and inlet areas. Here ignore the effect of frictional losses and take γ= 1.3.
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