Similar articles

Abstract: The nozzle is a critical component responsible for generating most of the net thrust in a scramjet engine. The quality of its design directly affects the performance of the entire propulsion system. However, most turbulence models struggle to make accurate predictions for subsonic and supersonic flows in nozzles. In this study, we explored a novel model, the algebraic stress model k-kL-ARSM+J, to enhance the accuracy of turbulence numerical simulations. This new model was used to conduct numerical simulations of the design and off-design performance of a 3D supersonic asymmetric truncated nozzle designed in our laboratory, with the aim of providing a realistic pattern of changes. The research indicates that, compared to linear eddy viscosity turbulence models such as k-kL and shear stress transport (SST), the k-kL-ARSM+J algebraic stress model shows better accuracy in predicting the performance of supersonic nozzles. Its predictions were identical to the experimental values, enabling precise calculations of the nozzle. The performance trends of the nozzle are as follows: as the inlet Mach number increases, both thrust and pitching moment increase, but the rate of increase slows down. Lift peaks near the design Mach number and then rapidly decreases. With increasing inlet pressure, the nozzle thrust, lift, and pitching moment all show linear growth. As the flight altitude rises, the internal flow field within the nozzle remains relatively consistent due to the same supersonic nozzle inlet flow conditions. However, external to the nozzle, the change in external flow pressure results in the nozzle exit transitioning from over-expanded to under-expanded, leading to a shear layer behind the nozzle that initially converges towards the nozzle center and then diverges.

基于k-kL代数应力模型的三维截断偏置超声速尾喷管数值模拟

[1]Abdol-HamidKS, 2019. Development of kL-based linear, nonlinear, and full Reynolds stress turbulence models. AIAA Scitech 2019 Forum.

[2]Abdol-HamidKS, CarlsonJR, RumseyCL, 2016. Verification and validation of the k-kL turbulence model in FUN3D and CFL3D codes. The 46th AIAA Fluid Dynamics Conference.

[3]ArgrowBM, EmanuelG, 1988. Comparison of minimum length nozzles. Journal of Fluids Engineering, 110(3):283-288.

[4]BaysalO, 1992. Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle. NASA Contractor Report No. 4431, Langley Research Center, NASA, Washington, USA.

[5]BilligFS, KothariAP, 2000. Streamline tracing: technique for designing hypersonic vehicles. Journal of Propulsion and Power, 16(3):465-471.

[6]EdwardsC, SmallW, WeidnerJ, et al., 1975. Studies of scramjet/airframe integration techniques for hypersonic aircraft. The 13th Aerospace Sciences Meeting.

[7]GöingM, 1990. Nozzle design optimization by method-of-characteristics. The 26th Joint Propulsion Conference.

[8]GruhnP, HenckelsA, KirschsteinS, 2000. Flap contour optimization for highly integrated SERN nozzles. Aerospace Science and Technology, 4(8):555-565.

[9]GruhnP, HenckelsA, SiebergerG, 2002. Improvement of the SERN nozzle performance by aerodynamic flap design. Aerospace Science and Technology, 6(6):395-405.

[10]HerrmannH, RickH, 1991. Propulsion aspects of hypersonic turbo-ramjet-engines with special emphasis on nozzle/aftbody integration. ASME International Gas Turbine and Aeroengine Congress and Exposition, article V002T02A039.

[11]HirschenC, GülhanA, 2009. Infrared thermography and pitot pressure measurements of a scramjet nozzle flowfield. Journal of Propulsion and Power, 25(5):1108-1120.

[12]HirschenC, GülhanA, BeckWH, et al., 2008. Experimental study of a scramjet nozzle flow using the pressure-sensitive-paint method. Journal of Propulsion and Power, 24(4):662-672.

[13]HirschenC, GülhanA, BeckWH, et al., 2009. Measurement of flow properties and thrust on scramjet nozzle using pressure-sensitive paint. Journal of Propulsion and Power, 25(2):267-280.

[14]KoschelW, RickW, 1991. Design considerations for nozzles of hypersonic airbreathing propulsion. The 3rd International Aerospace Planes Conference.

[15]LedererR, KrügerW, 1993. Nozzle development as a key element for hypersonics. The 5th International Aerospace Planes and Hypersonics Technologies Conference.

[16]LiR, XuJL, YuKK, et al., 2021. Design and analysis of the scramjet nozzle with contact discontinuity. Aerospace Science and Technology, 113:106695.

[17]LiaoL, YanL, HuangW, et al., 2018. Mode transition process in a typical strut-based scramjet combustor based on a parametric study. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 19(6):431-451.

[18]LvZ, XiaZX, LiuB, et al., 2017. Preliminary experimental study on solid-fuel rocket scramjet combustor. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 18(2):106-112.

[19]MiaoJJ, CaiYW, WangD, et al., 2023. Optimum design method oriented thrust for over-under TBCC combined nozzle. Journal of Aerospace Power, 38(6):‍1367-1377 (in Chinese).

[20]NickersonG, DunnS, MigdalD, 1988. Optimized supersonic exhaust nozzles for hypersonic propulsion. The 24th Joint Propulsion Conference.

[21]QuanZB, XuJL, MoJW, 2012. Design of nonlinearly compressed SERN profile. Journal of Propulsion Technology, 33(6):951-955 (in Chinese).

[22]SeinerJM, PontonMK, JansenBJ, et al., 1992. The effects of temperature on supersonic jet noise emission. The 14th DGLR/AIAA Aeroacoustics Conference, p.295-307.

[23]SuXR, YuanX, 2017. Improved compressor corner separation prediction using the quadratic constitutive relation. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 231(7):618-630.

[24]WangSY, FuX, YangXL, et al., 2021. Progresses and challenges of high-order-moment turbulence closure. Advances in Mechanics, 51(1):29-61 (in Chinese).

[25]WenX, LiuJ, LiJ, et al., 2019. Design and numerical simulation of a clamshell-shaped inlet cover for air-breathing hypersonic vehicles. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(5):347-357.

[26]WilcoxDC, 1998. Turbulence Modeling for CFD. 2nd Edition. DCW Industries, La Cãnada, USA.

[27]YuHX, WeiZJ, 2023. Experimental and numerical investigation on design parameters of slot nozzles. Aerospace Science and Technology, 141:108509.

[28]YuKK, ChenYL, HuangS, et al., 2020. Inverse design method on scramjet nozzles based on maximum thrust theory. Acta Astronautica, 166:162-171.

[29]ZhangWH, LiuJ, DingF, et al., 2019. Novel integration methodology for an inward turning waverider forebody/inlet. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 20(12):918-926.

[30]ZhengJL, ChangJT, YangSB, et al., 2019. Trajectory optimization for a TBCC-powered supersonic vehicle with transition thrust pinch. Aerospace Science and Technology, 84:214-222.

[31]ZhuMJ, FuL, ZhangS, et al., 2018. Design and optimization of three-dimensional supersonic asymmetric truncated nozzle. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 232(15):2923-2935.