One-Dimensional Aerodynamic Heating and Ablation Prediction
Publication: Journal of Aerospace Engineering
Volume 32, Issue 4
Abstract
A simplified method is developed to calculate aerodynamic heating, ablation, and structural temperature response for a body traveling at high speeds. Mach number, altitude, and angle of attack are used as a function of time. Compressibility effects are considered by using Eckert’s reference temperature approach. Convective aerodynamic heating is calculated using external flow relations. Local pressure values are found through modified Newtonian theory. An approximate recession method that uses the heat of ablation is coupled to the aerodynamic heating. An in-depth solution accounts for material decomposition; however, it does not include the energy absorption of pyrolysis gases through the material. Reduction in the heat transfer coefficient caused by the transpiring gases is estimated. An Arrhenius equation is used to model the density of the ablative material. The method is examined for the validation of six different cases, and predictions are found to be in good agreement with experimental and analytical results. The verification studies indicate that the methodology is well suited for predicting the ablation and thermal response of a thermal protection system.
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References
Amar A. J. 2006. “Modeling of one-dimensional ablation with porous flow using finite control volume procedure.” Master’s thesis, North Carolina State Univ.
Anderson, J. D., Jr. 2006. Hypersonic and high temperature gas dynamics. Reston, VA: AIAA.
Arnas, A. Ö., D. D. Boettner, G. Tamm, S. A. Norberg, J. R. Whipple, M. J. Benson, and B. P. VanPoppel. 2010. “On the analysis of the aerodynamic heating problem.” J. Heat Transfer 132 (12): 124501. https://doi.org/10.1115/1.4001754.
Bertin, J. J. 1994. Hypersonic aerothermodynamics. Reston, VA: AIAA.
Bertin, J. J., and R. M. Cummings. 2003. “Fifty years of hypersonics: Where we’ve been, where we’re going.” Prog. Aerosp. Sci. 39 (6–7): 511–536. https://doi.org/10.1016/S0376-0421(03)00079-4.
Bianchi, D. 2007. “Modeling of ablation phenomena in space applications.” Ph.D. dissertation, Dept. of Mechanics and Aeronautics, Università di Roma “La Sapienza”.
Böhrk, H., C. Dittert, H. Weihs, T. Thiele, and A. Gülhan. 2014. “Sharp leading edge at hypersonic flight: Modeling and flight measurement.” J. Spacecraft Rockets 51 (5): 1753–1760. https://doi.org/10.2514/1.A32892.
Camberos, J. A., and L. Roberts. 1989. Analysis of internal ablation for the thermal control of aerospace vehicles. Stanford, CA: Dept. of Aeronautics and Astronautics, Stanford Univ.
Chapra, S. C., and R. P. Canale. 2015. Numerical methods for engineers. New York: McGraw-Hill Education.
Charubhun, W., and P. Chusilp. 2017a. “Application of thermal-solid interface CFD on thermal protection study for rocket warhead.” In Proc., 4th Asian Conf. on Defense Technology. Piscataway, NJ: IEEE.
Charubhun, W., and P. Chusilp. 2017b. “Aerodynamic heat prediction on a 15 degree cone-cylinder-flare configuration using 2D axisymmetric viscous transient CFD.” In Proc., 3rd Asian Conf. on Defense Technology. Piscataway, NJ: IEEE.
Covington, M. A. 2004. “Performance of a light-weight ablative thermal protection material for the stardust mission sample return capsule.” In Proc., 2nd Int. Planetary Probe Workshop, 257–268. Moffett Field, CA: NASA Ames Research Center.
Dec, J., and R. D. Braun. 2006. “An approximate ablative thermal protection system sizing tool for entry system design.” In AIAA Paper 2006-780. Reston, VA: AIAA.
Hankey, W. L. 1988. Re-entry aerodynamics. Reston, VA: AIAA.
Juliano, T. J., D. Adamczak, and R. L. Kimmel. 2015. “HIFiRE-5 flight test results.” J. Spacecraft Rockets 52 (3): 650–663. https://doi.org/10.2514/1.A33142.
Juliano, T. J., D. Adamczak, and R. L. Kimmel. 2014. “HIFiRE-5 flight test heating analysis.” In AIAA Paper 2014-0076. Reston, VA: AIAA.
Kasen, S. D. 2013. “Thermal management at hypersonic leading edges.” Ph.D. dissertation, Faculty of the School of Engineering and Applied Science, Univ. of Virginia.
Louderback, P. M. 2013. “A software upgrade of the NASA Aeroheating Code ‘MINIVER’.” M.Sc. thesis, Aerospace Engineering, Florida Institute of Technology.
MSC Software Corporation. 2017. Volume A: Theory and user information. Newport Beach, CA: MSC Software.
Quinn, R. D., and L. Gong. 2000. A method for calculating transient surface temperatures and surface heating rates for high-speed aircraft. NASA/TP-2000-209034. Washington, DC: NASA.
Riccio, A., F. Raimondo, A. Sellitto, V. Carandente, R. Scigliano, and D. Tescione. 2017. “Optimum design of ablative thermal protection systems for atmospheric entry vehicles.” Appl. Therm. Eng. 119: 541–552. https://doi.org/10.1016/j.applthermaleng.2017.03.053.
Simon, H. A., C. S. Liu, and J. P. Hartnett. 1966. The Eckert reference formulation applied to high-speed laminar boundary layers of nitrogen and carbon dioxide. NASA CR-420. Washington DC: NASA.
Yang, G., Y. Duan, C. Liu, and J. Cai. 2014. “Approximate prediction for aerodynamic heating and design for leading-edge bluntness on hypersonic vehicles.” In AIAA Paper 2014-1393. Reston, VA: AIAA.
Zander, F., R. G. Morgan, and U. Sheikh. 2013. “Hot-wall reentry testing in hypersonic impulse facilities.” AIAA J. 51 (2): 476–484. https://doi.org/10.2514/1.J051867.
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Information
Published In
Journal of Aerospace Engineering
Volume 32 • Issue 4 • July 2019
Copyright
©2019 American Society of Civil Engineers.
History
Received: Sep 13, 2018
Accepted: Feb 7, 2019
Published online: May 2, 2019
Published in print: Jul 1, 2019
Discussion open until: Oct 2, 2019
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