稀薄气体效应对乘波体飞行器气动力的影响

doi:10.7527/S1000-6893.2025.33039

Abstract

Abstract:

Hypersonic vehicles in large airspace and wide speed range have become one of the current research hotspots， and waveriders have attracted significant attention due to their high lift-to-drag ratio and relatively simple shape. However， there is little research on the aerodynamic characteristics of waveriders under high-altitude rarefied conditions. Since the flow field encompasses multiple regimes ranging from continuum to rarefied， the accurate prediction of aerodynamic characteristics remains a considerable challenge. Focusing on the rarefaction effect on aerodynamic characteristics of a waverider model， which is tested in the MARHy rarefied wind tunnel in France， the numerical simulations are performed using Direct Simulation Monte Carlo （DSMC） method， conventional Navier-Stokes （NS） equation， and DSMC data improved Navier Stokes （DiNS） model. By comparing with experiment data， the computational accuracy of the different methods is evaluated. The aerodynamic characteristics of the waverider in the near-continuum regime are analyzed， with particular emphasis on the local rarefaction effects within the flow field and their influence on aerodynamic performance. Furthermore， the effects of Mach number and angle of attack are systematically investigated. The results show that under the experimental conditions of Mach number 20 and Knudsen number 0.01， the error in drag predicted by the conventional NS equation with slip boundary conditions reaches as high as 39.19% compared to experimental data. The DiNS model can reduce this relative error to 3.95% by correcting the linear constitutive relationship； for this waverider， skin friction contributes approximately 97.14% of the total drag. A pronounced shear nonequilibrium effect exists within the boundary layer， which invalidates the linear constitutive relations and causes the conventional NS equations to overpredict the skin friction. In addition， an increase in angle of attack leads to a significant increase in lift coefficient， a significant improvement in lift to drag ratio， and a more pronounced rarefaction effect. As the Mach number increases， the lift coefficient decreases significantly due to deviation from the design conditions， and the lift to drag ratio decreases significantly.

Key words: waverider, rarefaction effect, improved CFD model, DSMC method, wind tunnel test

CLC Number:

V211.3

Jingwen ZHANG, Jihui OU, Jie CHEN. Rarefaction effect on aerodynamic characteristics of waverider vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(19): 133039.

Figures/Tables 22

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工况	计算步数	时间步长Δt/s	升力系数C_L	升力系数误差/%	阻力系数C_D	阻力系数误差/%
A	4×10⁴	1×10^-7	-0.329		2.269
A1	5×10⁴	1×10^-7	-0.329		2.269
A2	4×10⁴	2×10^-7	-0.321	2.43	2.237	1.40
A3	4×10⁴	1×10^-8	-0.332	0.91	2.276	0.31

网格加密程度	N_x×N_y×N_z	Δx/（10^-5 m）	Δy/（10^-5 m）
粗网格	201×61×41	10	50.0
中等网格	241×91×61	2	1.0
细网格	261×121×81	1	0.5

网格加密程度	C_L	C_D
粗网格	-0.231 2	2.194 7
中等网格	-0.241 9	2.286 7
细网格	-0.242 8	2.306 7

计算方法	网格数	总CPU时间/h
DSMC	2 700 000	174.2
NS-noslip	1 337 791	35.4
NS-slip	1 337 791	37.8
DiNS-slip	1 337 791	41.8

Rarefaction effect on aerodynamic characteristics of waverider vehicle

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