The main objective of this paper is to study the effects of applying a heat source ahead of a supersonic mixed compression air intake. This intake has been designed for the freestream Mach number 2. Four parameters of the heat source, including its location, crosssectional shape, cross-sectional area, and heat generation rate, are investigated numerically to find a suitable heat source that enhances the performance of the intake. The research is conducted at the freestream Mach numbers of 1.8, 2, and 2.2. Total pressure recovery, mass flow ratio, flow distortion, and drag coefficient are considered as the intake performance parameters. Variation of the critical backpressure is further investigated. The results show that a bow shock is formed around the heat source that affects the intake shock system and can have desirable effects on most of the performance parameters and the critical backpressure at different freestream Mach numbers. It is also observed that the heat source location is the most effective parameter of the heat source, and should be selected meticulously.

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