Computational Investigation of the Effects of Heat Source Position on the Performance of a Mixed Compression Supersonic Intake

Document Type : Research Article

Authors

Mechanical Engineering Department, Faculty of Engineering, Ferdowsi University of Mashhad, Iran

Abstract

Investigation of the intake performance is one of the most important topics in the aerodynamic design of the aerial vehicles. In this study, the performance of a supersonic axisymmetric mixed compression intake, which was designed for the free stream Mach number of 2, has been investigated at zero degrees angle of attack. Then by applying a heat source and changing its position, the effects of this source on the intake performance have been studied. The flow has been simulated by a computational fluid dynamics code. The experimental results which were achieved in the wind tunnel at Imam Hossein University have been used to validate the numerical simulation. Results show that a heat source located at the proper location could have desirable effects on the total pressure recovery, mass flow ratio and drag coefficient of the intake. The critical back pressure ratio also increases, which widens the intake operating region. However, the flow distortion will increase a bit. At the design Mach number and critical condition, 9.68% increase in total pressure recovery, 26.6% decrease in drag coefficient, 16.16% increase in mass flow ratio, 8.7% increase in critical back pressure ratio and 17.13% increase in flow distortion have been observed.

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References

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Amirkabir Journal of Mechanical Engineering
Volume 52, Issue 4
July 2020
Pages 1023-1036

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