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8 - Aerothermodynamic Testing and Hypersonic Physics

Published online by Cambridge University Press:  12 October 2023

Zonglin Jiang  and
Randy S. M. Chue
Zonglin Jiang
Affiliation:
Chinese Academy of Sciences, Beijing
Randy S. M. Chue
Affiliation:
Nanyang Technological University, Singapore
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Summary

The surrounding air flow around a hypersonic vehicle behaves quite differently from supersonic flows. The kinetic energy is converted into internal energy which can increase the flow temperature and induce endothermic reactions near the vehicle surface. It is a challenge to develop flow diagnostic and aerodynamic measurement technologies with high precision for high-enthalpy wind tunnel tests. There are, generally, three types of measurement technologies widely used in exploring high-enthalpy flows, including heat-transfer measurement, aerodynamic balance, and optical diagnostic techniques. In this chapter, hypersonic tests with the aforementioned measurement technologies are summarized to demonstrate the progress on high-enthalpy flow experiments. Four kinds of experiments are included here, and the topics are aerodynamic force and moment tests, aerothermal heating measurements, hypersonic boundary-layer flow diagnostics, and supersonic combustion and scramjet engine tests. Actually, there are a lot of interesting topics, but these four are important not only to understand aerothermodynamic physics but also to support the development of hypersonic vehicles.

Keywords

hypersonic testaerodynamic forces and momentumaerodynamic heatinghypersonic boundary layersupersonic combustion tests
Type
Chapter
Information
Theories and Technologies of Hypervelocity Shock Tunnels , pp. 236 - 297
Publisher: Cambridge University Press
Print publication year: 2023

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References

AIAA. (2003). Recommended Practice: Calibration and Use of Internal Strain-Gage Balances with Application to Wind Tunnel Testing. AIAA Paper 2003-R-091.Google Scholar
AIAA-Guide. (2003). Assessing Experimental Uncertainty. AIAA S-071A-1999 (AIAA Paper 2003-G-045).Google Scholar
AIAA-Standard. (1999). Assessment of Experimental Uncertainty with Application to Wind Tunnel Testing. AIAA Paper No. 99-S-071A.Google Scholar
Alexander, F. (2011). Transition and Stability of High-Speed Boundary Layers. Annual Review of Fluid Mechanics, 43, 79–95.Google Scholar
Anderson, J. D. (2006). Hypersonic and High-Temperature Gas Dynamics, 2nd ed. Reston, VA: AIAA.Google Scholar
Arrington, P. J., Joiner, R. J., and Henderson, A. J. (1954). Longitudinal Characteristics of Several Configurations at Hypersonic Mach Numbers in Conical and Contoured Nozzles. NASA TN D-2489.Google Scholar
Bernstein, L. (1975). Force Measurement in Short-duration Hypersonic Facilities. AGARDograph No. 214.Google Scholar
Bertin, J. J. and Cummings, R. M. (2003). Fifty Years of Hypersonics: Where We’ve Been, Where We’re Going. Progress in Aerospace Sciences, 39, 511–536.Google Scholar
Bertin, J. J. and Cummings, R. M. (2006). Critical Hypersonic Aerothermodynamic Phenomena. Annual Review of Fluid Mechanics, 38, 129–157.Google Scholar
Buttsworth, D. R. (2001). Assessment of Effective Thermal Product of Surface Junction Thermocouples on Millisecond and Microsecond Time Scales. Experimental Thermal and Fluid Science, 25, 409–420.Google Scholar
Casper, K. M., Beresh, S. J., and Schneider, S. P. (2014). Pressure Fluctuations Beneath Instability Wave Packets and Turbulent Spots in a Hypersonic Boundary Layer. Journal of Fluid Mechanics, 756, 1058–1091.Google Scholar
Chen, H. (2000). Investigation on the Link-up between the Aerodynamic Force Data Measured in Supersonic and Hypersonic Wind Tunnel. ACTA Aerodynamica Sinica, 18(3), 345–349.Google Scholar
Cheng, H. K. (1959). Hypersonic Shock-layer Theory of a Yawed Cone and Other Three-dimensional Pointed Bodies. WADC TN 59–335.Google Scholar
Chynoweth, B. C., Edelman, J., Gray, K., Mckiernan, G., and Schneider, S. P. (2017). Measurements in the Boeing/AFOSR Mach-6 Quiet Tunnel on Hypersonic Boundary-Layer Transition. 47th AIAA Fluid Dynamics Conference.Google Scholar
Chynoweth, B. C., Schneider, S. P., Hader, C., Fasel, H., Batista, A., Kuehl, J., et al. (2019). History and Progress of Boundary-Layer Transition on a Mach-6 Flared Cone. Journal of Spacecraft Rockets, 56(2), 333–346.Google Scholar
Comte-Bellot, G. (1976). Hot-Wire Anemometry. Annual Review of Fluid Mechanics, 8, 209–231.Google Scholar
De Filippis, F., Savino, R., and Martucci, A. (2005). Numerical-Experimental Correlation of Stagnation Point Heat Flux in High Enthalpy Hypersonic Wind Tunnel. In AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. Capua, AIAA-2005-3277.Google Scholar
Fay, J. A. and Riddel, F. R. (1958). Theory of Stagnation Point Heat Transfer in Dissociated Air. Journal of Aeronautic Science, 25(2), 73–85.Google Scholar
Fluid Dynamics Panel Working Group 15. (1994). Quality Assessment for Wind Tunnel Testing. AGARD-AR-304.Google Scholar
Gao, Y. L. (2008). Study on Hypervelocity Flow Generation Techniques and Essential Hypersonic Phenomena. Ph.D Thesis, Institute of Mechanics, Beijing, China.Google Scholar
Gray, J. D. (1964). Summary Report on Aerodynamic Characteristics of Standard Models HB-1 and HB-2. AEDC-TDR-64-137.Google Scholar
Hirschel, E. H. (2005). Basics of Aerothermodynamics. Berlin: Springer.Google Scholar
Holden, M., Wadhams, T., MacLean, M., and Mundy, E. (2007). Experimental Studies in LENS I and X to Evaluate Real Gas Effects on Hypervelocity Vehicle Performance. 45th AIAA Aerospace Sciences Meeting and Exhibit: 204.Google Scholar
Hornung, H. G. (2010). Ground Testing for Hypersonic Flow, Capabilities and Limitations. RTO Technical Report. RTO-EN-AVT-186-1.Google Scholar
Hu, Z. M., Zhou, K., Peng, J., and Jiang, Z. L. (2017). Hypervelocity Test with a Detonation Driven Expansion Tube. The 31st International Symposium on Shock Waves, Nagoya, Japan, Jul. 13–18.Google Scholar
Jiang, Z. and Yu, H. (2014). Experiments and Development of Long-test-duration Hypervelocity Detonation-driven Shock Tunnel (LHDst). AIAA Paper 2014–1012.Google Scholar
Jiang, Z. L. (2014) Experiments and Development of Long Test Duration Hypervelocity Detonation-driven Shock Tunnel (LHDst). AIAA SciTech 2014, Maryland, USA.Google Scholar
Jiang, Z. L. and Yu, H. R. (2017). Theories and Technologies for Duplicating Hypersonic Flight Conditions for Ground Testing. National Science Review, 4(3), 290–296.Google Scholar
Jiang, Z. L., Hu, Z. M., Wang, Y. P., and Han, G. L. (2020). Advances in Critical Technologies for Hypersonic and High-enthalpy Wind Tunnel. Chinese Journal of Aeronautics, https://doi.org/10.1016/j.cja.2020.04.003.Google Scholar
Jiang, Z. L., Li, J. P., Zhao, W., and Liu, Y. (2012). Investigation into Techniques for Extending the Test-duration of Detonation-driven Shock Tunnels. Chinese Journal of Theoretical and Applied Mechanics, 44(5), 824–831. (in Chinese)Google Scholar
Jiang, Z. L., Wu, B., Gao, Y. L., Zhao, W., and Hu, Z. M. (2015). Development of the Detonation-driven Expansion Tube for Orbital Speed Experiments. Science China Technology Sciences, 58(4), 695–700.Google Scholar
Joarder, R. and Jagadeesh, G. (2003). A New Free Floating Accelerometer Balance System for Force Measurements in Shock Tunnels. Shock Waves, 13, 409–412.Google Scholar
Kammeyer, M. E. (1999). Uncertainty Analysis for Force Testing in Production Wind Tunnels. In 1st International Symposium on Strain Gauge Balances.Google Scholar
Kuehl, J. J. (2018). Thermoacoustic Interpretation of Second-Mode Instability. AIAA Journal, 56, 1–8.Google Scholar
Ladson, C. and Blackstock, T. (1962). Air-helium simulation of the aerodynamic force Coefficients of Cones at Hypersonic Speeds. NASA TN D-1473.Google Scholar
Laurence, S. J. and Karl, S. (2010). An Improved Visualization-Based Force-measurement Technique for Short-duration Hypersonic Facilities. Experiments in Fluids, 48, 949–965.Google Scholar
Li, J. P., Chen, H., Zhang, S. Z., Zhang, X., and Yu, H. (2017). On the Response of Coaxial Thermocouples for Transient Aerodynamic Heating Measurements. Experimental Thermal and Fluid Science, 86, 141–148.Google Scholar
Li, Q., Jiang, T., and Chen, S. Y. (2019). Measurement Technology and Measuring of Boundary Layer Transition in Shock Tunnel. Acta Aeronautica et Astronautica Sinica, 40(7), 122740Google Scholar
Li, S. X., Shi, J., and Guo, X. (2016). Experimental Study of Boundary Layer Features on a Flat Plate in High Speed Flow. Physics of Gases, 1(6), 1–4.Google Scholar
Li, X., Yu, C., and Tong, F. (2018). Direct Numerical Simulation of Hypersonic Boundary-layer Transition of Blunt Cones. Tenth International Conference on Computational Fluid Dynamics Barcelona, Spain.Google Scholar
Liu, M. K., Han, G. L., and Jiang, Z. L. (2019). Experimental Investigation on Plate Boundary Layer Transition in JF-12 Hypersonic Shock Tunnel. Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019).Google Scholar
Lu, F. K. and Marren, D. E. (2002). Advanced Hypersonic Test Facilities. Progress in Astronautics Vol. 198.Google Scholar
MacWherter, M., Noack, R. W., and Oberkampf, W. L. (1986). Evaluation of Boundary-layer and Parabolized Navier-Stokes Solutions for Reentry Vehicles. Journal of Spacecraft and Rockets, 23(1), 70–78.Google Scholar
Marineau, E.C., Grossir, G., Wagner, A., Leinemann, M., Radespiel, R., Tanno, H., et al. (2019). Analysis of Second-Mode Amplitudes on Sharp Cones in Hypersonic Wind Tunnels. Journal of Spacecraft Rockets, 3(2), 1–12.Google Scholar
Marineau, E., MacLean, M., Mundy, E., and Holden, M. (2012). Force Measurements in Hypervelocity Flows with an Acceleration Compensated Strain Gage Balance. Journal of Spacecraft and Rockets, 49(3), 474–482.Google Scholar
Martinez, B., Bastide, M., and Wey, P. (2014). Free Flight Measurement Technique in Shock Tunnel. In Proceedings of the 30th Aerodynamic Measurement Technology and Ground Testing Conference (Atlanta, USA).Google Scholar
Maus, J. R., Griffith, B. J., Szema, K. Y., and Best, J. T. (1984). Hypersonic Mach Number and Real Gas Eon Space Shuttle Orbiter Aerodynamic. Journal of Spacecraft and Rockets, 21, 136–141.Google Scholar
Mee, D. J., Daniel, W. J. T., and Simmons, J. M. (1996). Three-Component Force Balance for Flows of Millisecond Duration. AIAA Journal, 34(3), 590–595.Google Scholar
Mikhailov, V. V., Neiland, V. Ya., and Sychev, V. V. (1971). The Theory of Viscous Hypersonic Flow. Annual Review of Fluid Mechanics, 3, 371–396.Google Scholar
Morkovin, M., Reshotko, E., and Herbert, T. (1994). Transition in Open Flow System-A Reassessment. Bulletin of American Physical Society, 39, 1882.Google Scholar
Naumann, K. and Ende, H. (1990). A Novel Technique for Aerodynamic Force Measurements in Shock Tubes. AIP Conference Proceedings, 208, 653–658.Google Scholar
Naumann, K., Ende, H., Mathieu, G., and George, A. (1993) Millisecond Aero-dynamic Force Measurement with Side-jet Model in the ISL Shock Tunnel. AIAA Journal, 31, 1068–1074.Google Scholar
Park, C. (2013). Hypersonic Aerothermodynamics: Past, Present and Future. International Journal of Aeronautical and Space Sciences, 14(1), 1–10.Google Scholar
Parziale, N. J., Shepherd, J. E., and Hornung, H. G. (2014). Free-stream Density Perturbations in a Reflected-shock Tunnel. Experiments in Fluids, 55, 1665.Google Scholar
Penland, J. A. (1961). Aerodynamic Force Characteristics of a Series of Lifting Cone and Cone-cylinder Configurations at m = 6.83 and Angles of Attack up to 130 degree. NASA TN D-840.Google Scholar
Rasmussen, M. (1994). Hypersonic Flow. New York: John Wiley & Sons.Google Scholar
Robinson, M. J., Schramm, J. M., and Hannemann, K. (2011). Design and Implementation of an Internal Stress Wave Force Balance in a Shock Tunnel. CEAS Space Journal, 1, 45–57.Google Scholar
Roediger, T., Knauss, H., Estorf, M., Schneider, S. P., and Smorodsky, B. V. (2009). Hypersonic Instability Waves Measured Using Fast-Response Heat-Flux Gauges. Journal of Spacecraft Rockets, 46, 266–273.Google Scholar
Rose, P. H. (1958). Development of the Calorimeter Heat Transfer Gauge for Use in Shock Tubes. Review of Scientific Instruments, 29, 557.Google Scholar
Sahoo, N., Mahapatra, D. R., Jagadeesh, G., Gopalakrishnan, S., and Reddy, K. P. J. (2003). An Accelerometer Balance System for Measurement of Aerodynamic Force Coefficients Over Blunt Bodies in a Hypersonic Shock Tunnel. Measurement Science and Technology, 14, 260–272.Google Scholar
Sanderson, S. R., Simmons, J. M. and Tuttle, S. L. (1991). A Drag Measurement Technique for Free-piston Shock Tunnels. AIAA Paper 91–0540.Google Scholar
Sanderson, S. R. and Sturtevant, B. (2002). Transient Heat Flux Measurement Using a Surface Junction Thermocouple. Review of Scientific Instruments, 73, 2781.Google Scholar
Saravanan, S., Jagadeesh, G., and Reddy, K. P. J. (2009) Aerodynamic Force Measurement Using 3-component Accelerometer Force Balance System in a Hypersonic Shock Tunnel. Shock Waves, 18, 425–435.Google Scholar
Schlichting, H. and Gersten, K. (2017). Boundary-Layer Theory. Springer Berlin Heidelberg.Google Scholar
Schultz, D. L. and Jones, T. V. (1973). Heat-transfer Measurements in Short-duration Hypersonic Facilities. AGARD AG-163.Google Scholar
Seiler, F., Mathieu, G., George, A., Srulijes, J., and Havermann, M.(2005) Development of a Free Flight Force Measuring Technique (FFM) at the ISL Shock Tube Laboratory. In 25th International Symposium on Shock Waves, ISSW 25, Bangalore, India. ISL Report PU 620/2005.Google Scholar
Spadaccini, L. J. and Colket III, M. B. (1994). Ignition Delay Characteristics of Methane Fuels. Progress in Energy and Combustion Science, 20, 431–460.Google Scholar
Stalker, R. J. (1967). A Study of the Free-piston Shock Tunnel. AIAA Journal, 5, 2160–2165.Google Scholar
Tani, I. (1969). Boundary-Layer Transition. Annual Review of Fluid Mechanics, 1, 169–196.Google Scholar
Tanno, H., Komuro, T., Sato, K., Fujita, K., and Laurence, S.J. (2014). Free-flight measurement technique in the free-piston shock tunnel HIEST. Review of Scientific Instruments, 85, 045112.Google Scholar
Tanno, H., Komuro, T., Sato, K., Itoh, K., and Yamada, T. (2013). Free-flight Tests of Reentry Capsule Models in Free-piston Shock Tunnel. AIAA Paper 2013–2979.Google Scholar
Tashiro, Y., Biwa, T., and Yazaki, T. (2005). Calibration of a Thermocouple for Measurement of Oscillating Temperature. Review of Scientific Instruments, 76, 124901.Google Scholar
Wang, Q., Li, J. P., Zhao, W., and Jiang, Z. L. (2016a). Comparative Study on Aerodynamic Heating Under Perfect and Nonequilibrium Hypersonic Flows. Science China, 59, 624701.Google Scholar
Wang, Q., Olivier, H., Einhoff, J., Li, J., and Zhao, W. (2019). Influence of Test Model Material on the Accuracy of Transient Heat Transfer Measurements in Impulse Facilities. Experimental Thermal and Fluid Science, 104, 59–66.Google Scholar
Wang, Y. P., Liu, Y. F., Luo, C. T., and Jiang, Z. L. (2016b). Force Measurement Using Strain-gauge Balance in a Shock Tunnel with Long Test Duration. Review of scientific instruments, 87(5), 55108.Google Scholar
Wey, P., Srulijes, J., Bastide, M., Martinez, B., and Gnemmi, P. (2012). Determination of Aerodynamic Coefficients from Shock Tunnel Free Flight Trajectories. In Proceedings of the 28th Aerodynamic Measurement Technology, Ground Testing and Flight Testing Conference 2102, Vol. 2. Reston, VA: AIAA, pp. 949–957.Google Scholar
Willeke, K. and Bershader, D. (1973). An Improved Thin-film Gauge for Shock-tube Thermal Studies. Review of Scientific Instruments, 44, 22.Google Scholar
Woods, W. C, Arrington, J. P., and Hamilton, H. H. (1983). A Review of Preflight Estimates of Real-gas Effects on Space Shuttle Aerodynamic Characteristics. In Shuttle Performance: Lessons Learned. NASA Conf. Publ. 2283.Google Scholar
Wu, B. (2012). Study on the Interaction of Strong Shock Wave and the Hypervelocity Experimental Method. Ph.D. Thesis. Institute of Mechanics, Beijing, China.Google Scholar
Wu, S., Shu, Y. H., Li, J. P., and Yu, H. R. (2014). An Integral Heat Flux Sensor with High Spatial and Temporal Resolutions. Chinese Science Bulletin, 59, 2484–2489 (in Chinese).Google Scholar
Xiong, Y., Yu, T., Lin, L., Zhao, J. and Wu, J. (2020). Nonlinear Instability Characterization of Hypersonic Laminar Boundary Layer. AIAA Journal, 58(12), 5254–5263.Google Scholar
Yi, S., He, L., Zhao, Y., Tian, L., and Cheng, Z. (2009). A Flow Control Study of a Supersonic Mixing Layer Via NPLS. Science in China Series G: Physics, Mechanics and Astronomy, 52, 2001–2006.Google Scholar
Yu, H., Esser, B., Lenartz, M., and Grönig, H. (1992). Gaseous Detonation Driver for a Shock Tunnel. Shock Waves, 2, 245–254.Google Scholar
Zhang, H. (2004). Hypersonic Aerodynamic Test. Beijing, China: National Defense Industry Press.Google Scholar
Zhao, Y., Yi, S., Tian, L., and Cheng, Z. (2009). Supersonic Flow Imaging Via Nanoparticles. Science in China Series E: Technological Sciences, 52, 3640.Google Scholar
Zhong, X. (2009). Numerical Simulation of Hypersonic Boundary Layer Receptivity and Stability on Blunt Circular Cones. 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.Google Scholar
Zhou, K., Peng, J., Ou, D. B., and Jiang, Z. L. (2020). Experimental Study on Aerodynamic Heat and Wall Catalytic Effects of Hypervelocity Flow. Scientia Sinica Technologia, 50, 1095–1101 (in Chinese).Google Scholar
Zhou, K., Wang, Q., Hu, Z. M., and Jiang, Z. (2016a). Performance Study of a Detonation-driven Expansion Tube. Acta Aeronautica ET Astronautica Sinica, 37, 810–816 (in Chinese).Google Scholar
Zhou, K., Yuan, C. K., Hu, Z. M., and Jiang, Z. (2016b). Test Flow Analysis and Upgrade of the JF-16 Expansion Tube. Acta Aeronautica ET Astronautica Sinica, 37, 3296–3303 (in Chinese).Google Scholar
Zhu, Y., Chen, X., Wu, J., Chen, S., Lee, C., and Gad-El-Hak, M. (2018). Aerodynamic Heating in Transitional Hypersonic Boundary Layers: Role of Second-mode Instability. Physics of Fluids, 30, 011701.Google Scholar

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