A rapid assessment approach on the incoming flow parameter matching schemes of a combustion wind tunnel has been established based on basic aerodynamic laws. Shock and isentropic compression configurations are introduced to quantify the deviation range of the aerodynamic characteristics to true flight in multiple matching conditions. The most significant findings of the study may be summarized as follows: 1. In M-matched conditions, the deviation of aerodynamic forces for shock compression is less than 2 %. The selection of the energy- and pressure-related parameters to match makes little contribution to this deviation. For isentropic compression case, difference is much larger when the compression ratio goes higher. For practical configurations, the mismatch of the wave structures could be considerably large. 2. In P_0Q-matched conditions, the reduction of the incoming flow Mach number weakens the vitiation effects and it is easier to obtain the aerodynamic force and wave structure closer to real flight. 3. Numerical simulation of the more practical situation confirms the theoretical analysis and further indicates that if appropriate flow parameter matching scheme is selected, combustion wind tunnels can reproduce the aerodynamic characteristics closer to true flight than conventional ones.
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