超燃衝壓引擎為當前重要發展技術之一，其實驗不易且花費昂貴，需配合數值模擬以降低風險與成本，其流場包括紊流、震波、燃燒與混合等複雜之物理現象，有著許多可研究與探討之議題。故本文應用計算流體力學軟體結合Flamelet燃燒化學模型並考慮 Jachimowski (2006) 所提出的32條氫氧反應式應用於模擬分析高超音速紊流流場與高超音速紊流燃燒流場之流場特性，並探討SST-κ-ω紊流模型與LES紊流模型個別應用於高超音速紊流流場與高超音速紊流燃燒流場之差異與優劣。本文以澳洲昆斯蘭大學所設計之HyShot-II為計算模型，使用結構網格建立完整的HyShot-II計算模型，模擬空氣以7.4馬赫之速度進入HyShot-II於海拔23公里高空條件下之超音速紊流無反應流場與超音速紊流燃燒反應流場。本文先建立二維之計算模型，因HyShot-II之側面壁面所產生之震波可能為一個影響流場之重要因素，進而建立三維之計算模型，進行二維與三維流場之比較，並以高馬赫數之紊流流場與紊流燃燒流場之模擬分析結果與Rana等人的模擬結果及Karl等人高焓風洞的實驗值比對來驗證本文數值模擬方法之準確性。本文二維模擬結果與Karl等人高焓風洞的實驗值趨勢相符，但因為二維流場忽略側面邊壁震波之影響，導致燃燒室出口與噴嘴下壁面之壓力略低於實驗值。在三維計算模型中，分別探討了有無側面邊壁導角對流場之影響，並將模擬結果與實驗值比對。從結果中可知，以LES紊流模型結合32條反應式之Flamelet火焰模型模擬計算三維考慮邊壁導角超音速紊流燃燒流場準確度較高。

Scramjet is one of the current important developments of technology. The experiment is difficult and expensive. It has to reduce the risk and cost with numerical simulation. General supersonic flow field is complex, due to the mixing and combustion of the injected fuel in the high-speed flow and the interaction between the shock wave and the boundary layer. There are many investigations and issues to the supersonic combustion flow. This dissertation describes the application of CFD code to the hypersonic non-reaction and combustion characteristics of the HyShot-II scramjet employing the SST-κ-ω or LES turbulence model and the Flamelet reaction model with the hydrogen-oxygen 32-step reaction model proposed by Jachimowski (2006). The HyShot-II scramjet was originally designed by the University of Queensland. In the present study, a two dimensional CFD analysis is conducted for the HyShot-II scramjet using structured grids at a flow Mach number of 7.4 and an altitude of 23 km. The numerical results show that the predicted pressure distribution on the bottom wall is less than the experimental one at the outlet of the combustion chamber and the nozzle, since the bow shock of the side wall is ignored for the two dimensional CFD analysis. Therefore, the three-dimensional effect has also been investigated in the present dissertation. The numerical results of 2D and 3D can be compared with the CFD results of Rana and the experimental one of Karl. The predicted numerical results are in qualitative agreement with Rana's simulation results and Karl's experimental ones, validating the present numerical model. And then, this dissertation discusses the effect of lead angle of side wall for turbulent flow. The simulation results of three dimension with lead angle of side wall also show that the LES model with the hydrogen-oxygen 32-step reaction model leads to better accuracy in the prediction of the supersonic combustion flow.

1.Guerra, R and Waidmann, W, “An Experimental Investigation of the Combustion of a Hydrogen Jet Injected Parallel in a Supersonic Air Stream”, AIAA Paper , pp. 1-11, 1991.
2.Waidmann, W and Brummund, U., “Supersonic Combustion of Hydrogen/Air in a Scramjet Combustion Chamber”, Space Technol, Vol.15, NO.6, pp.421-429, 1995.
3.Aso, S., Okuyama, S., Kawai, M., and Ando, Y., “Experiment Study on Mixing Phenomena in Supersonic Flows with Slot Injection,” AIAA Paper, 1991.
4.Takahashi, S and Wakai, K., “Effect of Combustion on Flowfield in a Model Scramjet Combustor”, Combustion Institute, pp.2143-2150, 1998.
5.Kumaran, K and Babu, V., “Investigation of the Effect of Chemistry Model on the Numerical Predictions of the Supersonic Combustion of Hydrogen”, Combustion and Flame, January, 2009.
6.Rajasekaran, A and Babu, V., “Numerical Simulation of Three-Dimension Reacting Flow in a Model Supersonic Combustor”, Journal of Propulsion and Power, Vol.22, NO.4, July-August, 2006.
7.Rizzeta, D., “Numerical Simulation of Slot Injection into a Turbulent Supersonic Stream,”AIAA Paper, 1992.
8.Chenault, C.F and Beran, P.S., “K- and Reynolds Stress Turbulence Model Comparisons for Two-Dimensional Injection Flows,”AIAA Journal, Vol. 36, No. 8, August, 1998.
9.Menter, F. R., “Two Equation Eddy-Viscosity Turbulence Models for Engineering Applications”, AIAA Journal, Vol.32, NO.8, August, 1994.
10.Bartosiewicz, Y., Aidoun, Z., Desevaux, P., and Mercadier, Y., “Numerical and Experiment Investigation on Supersonic Ejector”, International Journal of Heat and Fluid Flow, Vol. 26, pp.56-70, 2005.
11.Berglund, M and Fureby, C., “ LES of Supersonic Combustion in a Scramjet Engine Model”, Proceedings of the Combustion Institute 31, pp. 2497–2504, 2007.
12.Oevermann, M., “Numerical Investigation of Turbulent Hydrogen Combustion in a Scramjet Using Flamelet modeling”, Aerospace Science and Technology, Vol.4, pp463-480, 2000.
13.Polivanov, P. A., “Numerical Simulation of Shock Wave/Turbulent Boundary Layer Interaction Using Fluent 6.3”, International Conference on Methods of Aerophysical Research, ICMAR, 2008.
14.Wepler, U., and Koschel, W., “Numerical Investigation of Turbulent Reacting Flows in a Scramjet Combustor Model”, AIAA Paper No. 3572, 2002.
15.Alexander, D. C and Siislian, J. P., “Computational Study of the Propulsive Characteristics of a Scramjet Engine”, Journal of Propulsion and Power, Vol.24, No.1, January-February, 2008.
16.Tabet, F., “Hydrogen-Hydrocarbon Turbulent Non-Premixed Flame Structure”, International Journal of Hydrogen Energy 34, pp.5040-5047, 2009.
17.Ali, M., Fujiwara, T., and Leblanc, J.E., “Influence of Main Flow Inlet Configuration on Mixing and Flameholding in Transverse Injection into Supersonic Airstream”, International Journal of Engineering Science, Vol.38, pp.1161-1180, 2000.
18.Ali, M., Islam, A.K.M-S., and Ahmed, S., “Mixing and Flame Holding with Air Inlet Configuration in Scramjet Combustor”, International Journal of Heat and Mass Transverse, Vol.31, pp.1187-1198, 2004.
19.Ali, M., and Islam, A.K.M.-S., “Study on Main Flow and Fuel Injector Configurations for Scramjet Applications”, International Journal of Heat and Mass Transverse, Vol.49, pp.3634-3644, 2006.
20.Furudate, M, Lee, M., and Jeung, I., “Computation of HyShot Scramjet Flows in the T4 Experiments”, AIAA Paper No. 3353, 2005.
21.Jeung, I. S., and Choi, J. Y., “Numerical Simulation of Supersonic Combustion for Hypersonic Propulsion,” 5th Asia-Pacific Conference on Combustion, 2005.
22.Choi, J.Y., Ma, F., and Yang, V., “Combustion Oscillations in a Scramjet Engine Combustor with Transverse Fuel Injection”, Proceedings of the Combustion Institute, Vol.30, pp.2851-2858, 2005.
23.Won, S. H., Jeung, I. S., and Choi, J. Y., “Turbulent Combustion Characteristics in HyShot Model Combustor with Transverse Fuel Injection,” AIAA Paper No. 5427, 2007.
24.Smart, M. K., Hass, N. E., and Paull, A.,“Flight Data Analysis of the HyShot2 Scramjet Flight Experiment,” AIAA Journal, Vol. 44,No. 10,2006.
25.Garner, A. D., Hannemann, K., Steelant, J., and Paull, A, “Ground Testing of the HyShot Supersonic Combustion Flight Experiment in HEG and Comparison with Flight Data,” AIAA Paper No. 3345, 2004.
26.Steelant, J., Mack, A., Hannemann, K., and Garner, A. D., “Comparison of Supersonic Combustion Tests with Shock Tunnels, Flight and CFD,” AIAA Paper No. 4684, pp. 1-14 , 2006.
27.Karl, S., Hannemann, K., Mack, A., and Steelant, J,“CFD Analysis of the HyShot-II Scramjet Experiments in the HEG Shock Tunnel,” AIAA Paper No. 2548, pp. 1-16, 2008.
28.Rana, Z. A., Thornber, B. J. R., and Drikakis, D., “Simulation of the HyShot-II(Scramjet) Model Using High-Resolution Methods,” AIAA Paper No. 4844, 2009.
29.Kindler, M., Blacha, T., Lempke, M., Gerlinger, and Aigner, M., “Numerical Investigations of Model Scramjet Combustors” Transactions of the High Performance Computing Center, pp. 153-166, 2009.
30.Pečnik, R., Terrapon, V. E., Ham, F., and Iaccarino, G., “Full System Scramjet Simulation,” Center for Turbulence Research, Annual Briefs, Stanford Univ, pp. 33-45, 2009.
31.Terrapon, V. E., Ham, F., Pečnik, R., and Pitsch, “A Flamelet-Based Model for Supersonic Combustion,” Annual Research Briefs, 2009.
32.Iaccarino, G., Pečnik, R., Terrapon, V. E., “Numerical Predictions of the Performance in Flight of an Air-Breathing Hypersonic Vehicle: HyShot-II,” IMECE Paper No. 40186, 2010.
33.Fureby, C., Chapuis, M., Fedina, E., and Karl, S., “CFD Analysis of the HyShot-II Scramjet Combustor,” Proceedings of the Combustion Institute, 2010.
34.FLUENT 6.3 User’s Guide , 2006.
35.Anderson, J.D., “Hypersonic and High-Temperature Gas Dynamics”, Amer Inst of Aeronautics, 2006.
36.Hannemann, K., Karl, S., Schramm, J. M., and Steenlant, J., “Methodology of a combined ground based testing and numerical modeling analysis of supersonic combustion flow paths,” Shock Waves, Vol.20, pp. 353-366, 2010.