Transactions of Nanjing University of Aeronautics & Astronautics
Drag Reduction Effect for Hypersonic Lifting-Body Vehicle with Counterflowing Jet
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Abstract:
This study takes the novel approach of using a counterflowing jet positioned on the nose of a lifting-body vehicle to explore its drag reduction effect at a range of angles of attack. Numerical studies are conducted at a free-stream Mach number of 8 in standard atmospheric conditions corresponding to the altitude of 40 km. The effects of jet pressure ratio and flying angles of attack on drag reduction of the model are systematically investigated. Considering the reverse thrust generated from the counterflowing jet, the drag on the nose at hypersonic speeds could be reduced up to 66%. The maximum lift-to-drag ratio of the model is obtained at 6°; meanwhile, the counterflowing jet produces a drag reduction of 8.8% for the whole model. In addition to the nose, the counterflowing jet influences the drag by increasing the pressure drag of the model and reducing the skin friction drag of the first cone within 8°. The results show that the potential of the counterflowing jet as a means of active flow control for drag reduction is significant in the engineering application on hypersonic lifting-body vehicles.
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This work was supported by the Aeronautics Science Foundation (No.20163252037), the China Postdoctoral Science Foundation (No.2017M610325), the Natural Science Foundation of Jiangsu Province (No.BK20170771), and Fundamental Research Funds for the Central Universities (No.NP2017202).
Clc Number:
V221
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