A supersonic one-dimensional flow model for a microscale supersonic axial compressor was derived by applying the conservation laws of mass flow rate, momentum, and energy and the Reynolds transport theorem. For the convenience of early-stage aerodynamic design, we proposed a compressor performance map that shows the correlation between blade geometry, flow path geometry, and aerodynamic performance. As a result, we clarified the effects of changes in the positive and negative blade camber angles and expansion and contraction of the meridian flow path area on the total pressure ratio and adiabatic efficiency using a straight blade as a reference.
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