Modeling the Effects of Geometric Asymmetry on Aero-heating of the Ablative Noses
Abstractnoses by using the equivalent axisymmetric body (EAB) theory. This Code has been developed by researchers and the results of it have been validated by the various flight tests results. In the case of non-zero angle of attack or asymmetric surface ablation for each meriodinal plane, the equivalent meriodinal plane (EMP) is created for any meriodinal plane. The combinations of these planes constitute the EAB. The governing equations are solved for this body by using the non-equilibrium chemical reactions and the results of it are mapped to the main body. The solving of a typical nose during flight trajectory show that the convergence of this technique is very fast as compare to the user defined function (UDF) based on the fluent solvers. The results of this research are validated by the UDF and the relative error of it is less than 10 percent.
 Anderson, J., "Hypersonic and High Temperature Gas Dynamics", Second Edittion, McGraw-Hill, New York: ISBN:978-964-2751-04-4. pp. 325-346, (1989). Dejarnet, F.R., and Hamilton, H.H., "Inviscid Surface Streamlines and Heat Transfer on Shuttle-type Configuration", Journal of Spacecraft, Vol. 10, No. 5, pp. 314-321, (1973) . Carrel, B., Larry, W., and Thomas, J., "A Coupled Computer Code for the Transient Thermal Response and Ablation of Non-charring Heat Shields and Nose Tips", National Aeronautics and Space Administration, Vol. 4, No. 2, pp. 21-32, (1970) . Miner, E.W., "Computer User’s Guide for a Chemically Reacting Viscous Shock Layer Code", Vol. 8, No. 6, NASA CR-2551, pp. 24-32, (1975). Brykina, C., and Scott, D., "An Approximate Axisymmetric Viscous Shock Layer Aeroheating Method for Three-dimensional Bodies", AIAA NASA, TM198-207890, Vol. 11, No. 5, pp. 14-22, (1998). Dexygen1.6.1, G.R., "Ablation Modeling of Nose Section with UDF Linkage to Fluent Software", Journal of Thermophysicsand Heat Transfer, Vol. 14, No. 3, pp. 32-41, (2012). Chen, Y.K., and Melos, F.S., "Finite-rate Ablation Boundary Conditions for Carbon-phenolic Heat-shield", NASA Ames Research Canter, and Moffett Field, CA 94035-1000, Vol. 7, No. 3, pp. 41-54, (2013). Benjamin, S., Roy, H., Paul, H.S., Baumanb, T., and Oliver, T. A., "Modeling Hypersonic Entry with the Fully-implicit Navier–Stokes (FIN-S) Stabilized Finite Element Flow Solve", Computers & Fluids, Vol. 15, No. 4, pp. 281–292, (2014). Doustdar, M.M., Mardani, M.M., and Ghadak, F., "Aero-heating Modelling on the Ablative Noses during Flight Trajectory", Aircraft Engineering and Aerospace Technology Journal, In Press, (2017). Doustar, M.M., Mardani, M., and Ghadak, F., " Investigation of Wall Catalytic Effects on the Aeroheation of Hypersonic Ablative Noses by Space Marching Method", Mechanic and Aerospace Engineering Journal of Imam Hossien University, Vol. 12, No. 1, pp. 15-26, (2017) (in Persian). Doustar, M.M., Mardani, M., and Ghadak, F., "Simulation of Temperature Distribution for Hypersonic Ablative Noses during Flight Trajectory by Space Marching Method", Modares Mechanical Engineering, Vol. 16, No. 12, pp. 163-174, (2016) (in Persian). Doustdar, M.M., Mardani, M.M., and and Ghadak, F., " Numerical Simulation of Radiance Effects on the Aerodynamic Heating of Ablative Nose with VSL-VBLS Method", Structure and Fluid Journal of Shahrod University, Vol. 7, No. 1, pp. 175-186, (2017) (in Persian). Ekert, E.R., "Engineering Relations for Heat Transfer and Friction in High-velocity Laminar and Turbolent Boundral-layer Flow Over Surfaces with Constant Pressure and Temperature", Trans. of the ASME, Vol. 78, No. 6, pp. 1273-1281, (1986). Zein, T.F., "Heat Transfer in the Melt Layer of a Simple Ablation Model", Journal of Thermophysicsand Heat Transfer, Vol. 13, No. 4, pp. 321-332, (1999). Rahimi, A.B., "Numerical Modeling of Charring Material Abalation with Considering Chemical Reaction, Mass Transfer and Surface Heat Transfer Effects", Journal of Thermophysicsand Heat Transfer, Vol. 15, No. 5, pp. 214-221, (2010). Karemian, H., Kafarian, M., and Azezi, M., "Hypersonic Flow Domain Sloution on the Missile Body with Consedering of High Temperature Effects to Calculate of Aeroheating", Research Project, Aerospace Engineering Complex of Amirkabir University, Iran, (2013)(In Persion). Howard, S., and Walter, E., "Heat-transfer and Pressure Distribution on Six Blunt Noses at a Mach Number of 2", NASA Research Memorandum, Bressette Langley Aeronautical Laboratory NASA, , Vol. 12, No. 4, pp. 21-28, (1975). Park, C., "Stagnation Point Ablation of Carbonaceous Flat Discs Part I", AIAA Journal, Vol. 21, No. 11, pp. 1588-1594, (1983). Park, C., "Calculation of Stagnation Point Heat Transfer for Pioneer Venus Probes", Proposed NASA Technical Memorandum, Vol. 8, No. 4, pp. 38-51, ( 2002). Emerson, D.R., and John, B., "Investigation of Heat and Mass Transfer in a Lid-driven Cavity under Non-equilibrium Flow Conditions", Numerical Heat Transfer, Part B, Vol. 5, No. 5, pp. 48-62, (2010) Kumar, A., "Laminar and Turbulent Flow Solutions with Radiation and Ablation Injection for Jovian Entry", AIAA Paper 80-0288, Vol. 12, No. 3, pp. 30-41, (1980). Reid, C.M., and Prausnitz, S.T., "The Properties of Gases and Liquids", McGraw-Hill, New York, (1977). Bradshaw, P.T., and Whitelaw, J., "Engineering Calculational Methods for Turbulent Flow", Academic Press, Vol. 16, No. 4, pp. 47-62, (1981). Marvin, J.D., "Turbulence Modeling for Computational Aerodynamics", AIAA Journal, Vol. 21, No. 7, pp. 941-955, (1983). Lomax, H., and Inouye, M., "Numerical Analysis of Flow Properties about Blunt Bodies Moving at Superonic Speeds in an Equilibrium Gas", NASA TR-R-204, Vol. 12, No. 5, pp. 54-70, (1964). Zhluktov, S.V., “Viscous Shock Layer Simulation of Airflow Past Ablating Blunt Body with Carbon Surface”, Journal of Thermo Physics and Heat Transfer Vol. 13, No. 1, pp. 442-462, (1999) .