Abstract
In the traditional investigations on the drag and heat reduction of hypersonic spiked models, only the aerodynamic calculation is performed, and the structural temperature cannot be obtained. This paper adopted the loosely coupled method to study its efficiency of drag and heat reduction, in which the feedback effect of wall temperature rise on aeroheating is considered. The aeroheating and structural temperature were obtained by the CFD and ABAQUS software respectively. The coupling analysis of the hypersonic circular tube was carried out to verify the accuracy of the fluid field, the structural temperature, and the coupled method. Compared with experimental results, the calculated results showed that the relative errors of stagnation heat flux and stagnation temperature were 1.34% and 4.95% respectively, and thus the effectiveness of the coupled method was verified. Installing a spike reduced the total drag of the forebody. The spiked model with an aerodisk reduced the aeroheating of the forebody, while the model without an aerodisk intensified the aeroheating. The spiked model with a planar aerodisk had the best performance on drag and heat reduction among all the models. In addition, increasing the length of the spike reduced the drag and temperature of the forebody. With the increase of the length, the change rates of drag, pressure, heat flux, and temperature decreased gradually. Increasing the diameter of the aerodisk also reduced the temperature of the forebody, while the efficiency of forebody drag reduction first increased and then decreased. In conclusion, the heat and drag reduction must be considered comprehensively for the optimal design of the spike.
Highlights
Received: 12 November 2021The aeroheating and wave drag are the most important features of hypersonic vehicles [1,2]
The measurements of the drag reduction and thermal protection must be taken into consideration to ensure a better flight condition and to ensure the safety of hypersonic vehicles
The passive thermal protection system (TPS) has been widely used in hypersonic vehicles, it can not reduce aerodynamic drag
Summary
The aeroheating and wave drag are the most important features of hypersonic vehicles [1,2]. Used the numerical method to study used the experimental method to measure the heat flux of forebody with the opposingthe jet, influence of gas the adopted penetration on thermal protection efficiency. For further reducing the aeroheating andflux aerodynamic drag, scholars have dethe jet gas adopted was nitrogen. Signed some combined configurations by taking advantage of both the opposing jet and For further the aeroheating and aerodynamic some scholars have the spike [24,25,26,27,28,29].reducing. This paper mal coupled method, which can calculate the wall heat flux and structural temperature studied the thermal protection efficiency of the spiked model by adopting the fluid-thermal directly. Coupled method, which can calculate the wall heat flux and structural temperature directly
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