Aerodynamic Heat Prediction and Experimental Analysis of High-Speed Rocket Sleds

ZHOU Xuewen; ZHANG Chenhui; LV Shuiyan; LIU Jin; BA Weitao

doi:10.15892/j.cnki.djzdxb.2025.06.043

Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 6: 1310 - 1317

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.06.043

Academic article

Aerodynamic Heat Prediction and Experimental Analysis of High-Speed Rocket Sleds

ZHOU Xuewen ,
ZHANG Chenhui ^,^* ,
LV Shuiyan ,
LIU Jin ,
BA Weitao

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NORINCO GROUP Test and Measuring Academy,Huayin 714200,China

Received date: 2025-05-20

Online published: 2026-01-24

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Abstract

Aerodynamic heat research plays a crucial role in rocket sled testing,providing essential support for structural design and ensuring safety and reliability during high-speed operation.This paper focuses on the impact of spatial discretization schemes,turbulence models,and the height of the first normal grid layer on aerodynamic heat calculation results.Using a simplified model of typical a high-speed rocket sled,detailed aerodynamic heat calculations were conducted.The study analyzed the heat flux distribution at key locations on the sled body,revealing the interference mechanisms caused by track-reflected shock waves and fairings on the side of the vehicle.In addition,this paper conducts a quantitative analysis of the consistency between simulation and experimental results based on data from a single-track rocket sled test.The results indicate that:(1) For aerodynamic heat prediction in rocket sled,the Roe scheme is recommended for spatial discretization,the S-A model is preferred for turbulence modeling,and the height of the first normal grid layer should not exceed 1×10^-7m; (2) In the typical sled body,the peak heat flux in interference-free areas reaches 24050kW/m²,primarily concentrated in the connecting section.Interference are formed on the lower half of the conical section due to track-reflected shock waves,and significant interference is observed on the vehicle’s side due to the fairing,both of which lead to a substantial increase in local heat flux; (3) The maximum deviation between the simulated and experimental temperature results is 17.88%,demonstrating that the numerical method can be used for subsequent aerodynamic heat prediction of rocket sleds.The findings of this study provide important theoretical support for the engineering application of rocket sled testing.

Key words： rocket sled; numerical simulation; aerodynamic heat; heat flux density; experimental validation

Cite this article

ZHOU Xuewen , ZHANG Chenhui , LV Shuiyan , LIU Jin , BA Weitao . Aerodynamic Heat Prediction and Experimental Analysis of High-Speed Rocket Sleds[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(6) : 1310 -1317 . DOI: 10.15892/j.cnki.djzdxb.2025.06.043

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