1. Anderson, J.D.. Hypersonic and High Temperature Gas Dynamics, AIAA, 2006, Virginia, US.
2. Wang, Z., Sun, X., Huang, W., Li, S. and Yan, L. Experimental investigation on drag and heat flux reduction in supersonic/hypersonic flows: a survey, Acta Astronautica, 2016, 129, pp 95–110.
3. Alexander, S.R. Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds, NACA RM L6K08a, January 1947.
4. Bogdonoff, S.M. and Vas, I.E. Preliminary investigations of spiked bodies at hypersonic speeds, J Aerospace Sciences, 1959, 26, (2), pp 65–74.
5. Crawford, D.H. Investigation of the Flow Over a Spiked-Nose Hemisphere-Cylinder, NASA TN-D-118, December 1959.
6. Maull, D.J. Hypersonic flow over axially symmetric spiked bodies, J Fluid Mechanics, 1960, 8, (P.4), pp 584–92.
7. Wood, C.J. Hypersonic flow over spiked cones, J Fluid Mechanics, 1961, 12, (Pt. 4), pp 614–24.
8. Holden, M. Experimental studies of separated flows at hypersonic speeds. Part I—separated flows over axisymmetric spiked bodies, AIAA J, 1966, 4, (4), pp 591–599.
9. McGhee, R.J. and Staylor, W.F. Aerodynamic Investigation of Sharp Cone-Cylinder Spikes on 1200 Blunted Cones at Mach Numbers of 3, 4.5, and 6, NASA TN D-5201, 1969.
10. Staylor, W.F. Flow-Field Investigation for Large-Angle Cones with Short Spikes at a Mach Number of 9.6, NASA TN D-5754, 1970.
11. Yamauchi, M., Fujii, K. and Higashino, F. Numerical investigation of supersonic flows around a spiked blunt body, J Spacecraft and Rockets, 1995, 32, (1), pp 32–42.
12. Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E. Drag reduction for spike attached to blunt-nosed body at Mach 6, J Spacecraft and Rockets, 2010, 47, (1), pp 219–22.
13. Stadler, J.R. and Neilson, H.V. Heat Transfer from a Hemisphere Cylinder Equipped with Flow Separation Spikes, NACA TN-3287, 1954.
14. Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E. Experimental investigation on spiked body in hypersonic flow, Aeronautical J, 2008, 112, (1136), pp 593–8.
15. Jones, J.J. Experimental Drag Coefficients of Round Noses with Conical Wind-Shields at Mach Number 2.72, NACA RM L55E10, June 1955.
16. Beastall, D. and Turner, J. The Effect of a Spike Protruding in Front of a Bluff: Body at Supersonic Speeds, Aeronautical Research Council, R. & M. No. 3007, 1957.
17. Menezes, V., Saravanan, S. and Reddy, K.P.J. Shock tunnel study of spiked aerodynamic bodies flying at hypersonic Mach numbers, Shock Waves, 2002, 12, (1), pp 197–204.
18. Gopalan, J., Menezes, V., Reddy, K.P.J., Hashimoto, T., Sun, M., Saito, T. and Takayama, K. Flowfields of a large-angle, spiked blunt cone at hypersonic Mach numbers, Transactions of Japan Soc Aero Space Science, 2005, 48, (160), pp 110–116.
19. Heubner, L.D., Mitchell, A.M. and Boudreaux, E.J. Experimental Results on the Feasibility of an Aerospike for Hypersonic Missiles, AIAA paper, 95-0737, January 1995.
20. Gauer, M. and Paull, A. Numerical investigation of a spiked blunt nose cone at hypersonic speeds, J Spacecrafts and Rockets, 2008, 45, (3), pp 459–471.
21. Gerdroodbary, M.B. and Hosseinalipour, S.M. Numerical simulation of hypersonic flow over highly blunted cones with spike, Acta Astronautica, 2010, 67, pp 180–193.
22. Zhang, R., Huang, W., Yan, L., Li, L., Li, S. and Moradi, R. Numerical investigation of drag and heat flux reduction mechanism of the pulsed counterflowing jet on a blunt body in supersonic flows, Acta Astronautica, 2018, 146, pp 123–133.
23. Huang, W., Zhang, R., Yan, L., Ou, M. and Moradi, R. Numerical experiment on the flow field properties of a blunted body with a counterflowing jet in supersonic flows, Acta Astronautica, 2018, 147, pp 231–240.
24. Deng, F., Xie, F., Qin, N., Huang, W., Wang, L. and Chu, H. Drag reduction investigation for hypersonic lifting-body vehicles with aerospike and long penetration mode counterflowing jet, Aerospace Science and Technology, 2018, 76, pp 361–373.
25. Huang, W., Jiang, Y., Yan, L. and Liu, J. Heat flux reduction mechanism induced by a combinational opposing jet and cavity concept in supersonic flows, Acta Astronautica, 2016, 121, pp 164–171.
26. Sun, X., Guo, Z., Huang, W., Li, S. and Yan, L. Drag and heat reduction mechanism induced by a combinational novel cavity and counterflowing jet concept in hypersonic flows, Acta Astronautica, 2016, 126, pp 109–119.
27. Sun, X., Guo, Z., Huang, W., Li, S. and Yan, L. A study of performance parameters on drag and heat flux reduction efficiency of combinational novel cavity and opposing jet concept in hypersonic flows, Acta Astronautica, 2017, 131, pp 204–225.
28. Eghlima, Z. and Mansour, M. Drag reduction for the combination of spike and counterflow jet on blunt body at high Mach number flow, Acta Astronautica, 2017, 133, pp 103–110.
29. Gerdroodbary, M.B., Imani, M. and Ganji, D.D. Heat reduction using counterflowing jet for a nose cone with aerodisk in hypersonic flow, Aerospace Science and Technology, 2014, 39, pp 652–665.
30. Huang, W., Liu, J. and Xia, Z. Drag reduction mechanism induced by a combinational opposing jet and spike concept in supersonic flows, Acta Astronautica, 2015, 115, pp 24–31.
31. Eghlima, Z., Mansour, K. and Fardipour, K. Heat transfer reduction using combination of spike and counterflow jet on blunt body at high Mach number flow, Acta Astronautica, 2018, 143, pp 92–104.
32. Huang, W. A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations, J Zhejiang University – Science A (Applied Physics & Engineering), 2015, 16, (7), pp 309, 551–561.
33. Yadav, R. and Guven, U. Aerothermodynamics of a hypersonic projectile with a double-disk aerospike, Aeronautical J, 2013, 117, (1195), pp 913–928.
34. Yadav, R., Velidi, G. and Guven, U. Aerothermodynamics of generic re-entry vehicle with a series of aerospikes at nose, Acta Astronautica, 2014, 96, pp 1–10.
35. Kobayashi, H., Maru, Y. and Fukiba, K. Experimental study on aerodynamic characteristics of telescopic aerospikes with multiple disks, J Spacecraft and Rockets, 2007, 44, (1), pp 33–44.
36. Maru, Y., Kobayashi, H., Takeuchi, S. and Sato, T. Flow oscillation characteristics in conical cavity with multiple disks, J Spacecraft and Rockets, 2007, 44, (5), pp 1012–1020.
37. Liou, M.S A sequel to AUSM: AUSM+, J Computational Physics, 1996, 129, pp 364–382.
38. Roy, C.J. and Blottner, F.G. Review and assessment of turbulence models for hypersonic flows, Progress in Aerospace Sciences, 2006, 42, pp 469–530.
39. Roy, C.J. and Blottner, F.G. Assessment of One- and Two-Equation Turbulence Models for Hypersonic Transitional Flows, AIAA paper 2000-132, 38th AIAA Aerospace Sciences Meeting, Reno, NV, 10–13 January 2000.
40. Paciorri, R., Dieudonn, W., Degrez, G., Charbonnier, J.M. and Deconink, H. Exploring the validity of the Spalart–Allmaras turbulence model for hypersonic flows, J Spacecraft and Rockets, 1998, 35, (2), 121–126.
41. Spalart, P. and Allmaras, S. A one-equation turbulence model for aerodynamic flows, La Recherché Aerospatiale, 1994, 1, pp 5–21.
42. Dacles-Mariani, J., Zilliac, G.G., Chow, J.S. and Bradshaw, P. Numerical/experimental study of a wingtip vortex in the near field. AIAA J, 1995, 33, (9), pp 1561–1568.
43. Huang, W., Li, L., Yan, L. and Zhang, T. Drag and heat flux reduction mechanism of blunted cone with aerodisks, Acta Astronautica, 2017, 138, pp 168–175.
44. Roy, C.J. and Blottner, F.G. Further Assessment of One- and Two-Equation Turbulence Models for Hypersonic Transitional Flows, AIAA Paper 2001-0210.
45. Huang, W., Yan, L., Liu, J., Jin, L. and Tan, J. Drag and heat reduction mechanism in the combinational opposing jet and acoustic cavity concept for hypersonic vehicles, Aerospace Science and Technology, 2015, 42, pp 407–414.