Scramjet nozzle with adjustable cowl scheme
Author(s): PANG Li-na, XU Jing-lei, GE Jian-hui, Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics
Pages: 1685-1690
Year: 2015 Issue: 7
Journal: Journal of Aerospace Power
Keyword: scramjet; single expansion ramp nozzle; geometry adjustment; difference of pitch moment; wind tunnel experiment;
Abstract: The difference of cold/hot pitch moment will result in difficulty of vehicle attitude control when the hypersonic vehicle works at the relay point and cruising end point under the influence of cold and hot expansion conditions.To solve this problem,an adjustable cowl scheme was adopted and investigated,and also proven in effectively decreasing the difference of cold/hot pitch moment.The flow-field with different cowl angles was numerically simulated to obtain the performance parameters of nozzle.The results showed that,when the cowl angle was adjusted to 6°,the difference of cold/hot pitch moment was reduced by 29.57%and the thrust coefficient decreased only 0.42%in design Mach number 4.5.Finally,a wind tunnel experiment was carried out,and numerical simulation was performed based on the conditions of the wind tunnel experiment.The results of the simulation were in good agreement with experiment data,validating the effectiveness and correctness of the adjustment scheme and the results of numerical simulation.
Pages: 1685-1690
Year: 2015 Issue: 7
Journal: Journal of Aerospace Power
Keyword: scramjet; single expansion ramp nozzle; geometry adjustment; difference of pitch moment; wind tunnel experiment;
Abstract: The difference of cold/hot pitch moment will result in difficulty of vehicle attitude control when the hypersonic vehicle works at the relay point and cruising end point under the influence of cold and hot expansion conditions.To solve this problem,an adjustable cowl scheme was adopted and investigated,and also proven in effectively decreasing the difference of cold/hot pitch moment.The flow-field with different cowl angles was numerically simulated to obtain the performance parameters of nozzle.The results showed that,when the cowl angle was adjusted to 6°,the difference of cold/hot pitch moment was reduced by 29.57%and the thrust coefficient decreased only 0.42%in design Mach number 4.5.Finally,a wind tunnel experiment was carried out,and numerical simulation was performed based on the conditions of the wind tunnel experiment.The results of the simulation were in good agreement with experiment data,validating the effectiveness and correctness of the adjustment scheme and the results of numerical simulation.
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