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Coupled simulation of hypersonic flow and heat exchange is investigated. Moreover, structural stress based on pseudo static assumption is also studied. The unsteady Navier-Stokes equations are solved for the flow field, and SST k-ω model is used as the turbulent model. The unsteady heat conduction equation is solved for the structure. At the fluid-structure interface the flow field acquires temperature boundary condition from the structure and the structure temperature field obtains heat flux boundary condition from flow field. The method proposed here is proved by the slipstream experiment of the infinite circular pipe. The transformation of the temperature and stress of the two-dimensional circular pipe is analyzed in detail during aerodynamic heating. The results show that the high temperature field is gradually enlarged with the increase of aerodynamic heating time. At the same time the structural thermal strain is also gradually enhanced. The minimal deformed area will appear when θ is equal to 60°. The thermal deformation of circular pipe has very little effect on the flow field.
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Keywords:
- hypersonic /
- numerical simulation /
- aerodynamic heating /
- coupling
[1] Yan C, Yu J J, Li J Z 2006 Acta Aero. Sin. 24 125 (in Chinese) [阎超, 禹建军, 李君哲 2006 空气动力学学报 24 125]
[2] Li P F, Wu S P 2010 J. Aero. Power 25 1705 (in Chinese) [李鹏飞, 吴颂平 2010 航空动力学报 25 1705]
[3] Pramote D, Earl A T, Allan R W 1988 AIAA 1988-2245
[4] Allan R W, Michael S H 1987 AIAA 1987-1511
[5] Xia G, Liu X J, Cheng W K, Qin Z Z 2003 J. National Univ. Defense Tec. 25 35 (in Chinese) [夏刚, 刘新建, 程文科, 秦子增 2003 国防科技大学学报 25 35]
[6] Feng Y P, Cui J Z, Deng M X 2009 Acta Phys. Sin. 58 327 (in Chinese) [冯永平, 崔俊芝, 邓明香 2009 58 327]
[7] Yao X H, Han Q 2008 Acta Phys. Sin. 57 5056 (in Chinese) [姚小虎, 韩强 2008 57 5056]
[8] Zhou Y, Qian W Q, Deng Y Q, Ma M S 2010 Acta Aero. Sin. 28 213 (in Chinese) [周宇, 钱炜祺, 邓有奇, 马明生 2010 空气动力学报 28 213]
[9] Menter F R 1993 AIAA 1993-2906
[10] Peng Z Q, Zhang J F, Niu B, Mu D 2011 Mechanics Engineering 33 18 (in Chinese) [彭志琦, 张均峰, 牛斌, 穆丹 2011 力学与实践 33 18]
[11] Li P F, Wu S P 2010 Missiles Space Vehicle 6 34 (in Chinese) [李鹏飞, 吴颂平 2010 导弹与航天运载技术 6 34]
[12] Huang T, Mao G L, Jiang G Q, Zhou W J 2000 Acta Aero. Sin. 18 115 (in Chinese) [黄唐, 毛国良, 姜贵庆, 周伟江 2000 空气动力学报 18 115]
[13] Giles M B 1997 Int. J. Numerical Methods Fluids 25 421
[14] Ramon C, Houzeaux G 2006 Int. J. Numerical Methods Fluids 52 963
[15] Allen R W 1987 NASA TM-100484
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[1] Yan C, Yu J J, Li J Z 2006 Acta Aero. Sin. 24 125 (in Chinese) [阎超, 禹建军, 李君哲 2006 空气动力学学报 24 125]
[2] Li P F, Wu S P 2010 J. Aero. Power 25 1705 (in Chinese) [李鹏飞, 吴颂平 2010 航空动力学报 25 1705]
[3] Pramote D, Earl A T, Allan R W 1988 AIAA 1988-2245
[4] Allan R W, Michael S H 1987 AIAA 1987-1511
[5] Xia G, Liu X J, Cheng W K, Qin Z Z 2003 J. National Univ. Defense Tec. 25 35 (in Chinese) [夏刚, 刘新建, 程文科, 秦子增 2003 国防科技大学学报 25 35]
[6] Feng Y P, Cui J Z, Deng M X 2009 Acta Phys. Sin. 58 327 (in Chinese) [冯永平, 崔俊芝, 邓明香 2009 58 327]
[7] Yao X H, Han Q 2008 Acta Phys. Sin. 57 5056 (in Chinese) [姚小虎, 韩强 2008 57 5056]
[8] Zhou Y, Qian W Q, Deng Y Q, Ma M S 2010 Acta Aero. Sin. 28 213 (in Chinese) [周宇, 钱炜祺, 邓有奇, 马明生 2010 空气动力学报 28 213]
[9] Menter F R 1993 AIAA 1993-2906
[10] Peng Z Q, Zhang J F, Niu B, Mu D 2011 Mechanics Engineering 33 18 (in Chinese) [彭志琦, 张均峰, 牛斌, 穆丹 2011 力学与实践 33 18]
[11] Li P F, Wu S P 2010 Missiles Space Vehicle 6 34 (in Chinese) [李鹏飞, 吴颂平 2010 导弹与航天运载技术 6 34]
[12] Huang T, Mao G L, Jiang G Q, Zhou W J 2000 Acta Aero. Sin. 18 115 (in Chinese) [黄唐, 毛国良, 姜贵庆, 周伟江 2000 空气动力学报 18 115]
[13] Giles M B 1997 Int. J. Numerical Methods Fluids 25 421
[14] Ramon C, Houzeaux G 2006 Int. J. Numerical Methods Fluids 52 963
[15] Allen R W 1987 NASA TM-100484
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