Method for Splitting into Physicall Processes in Task of the Flow Over a Perspective High-Speed Vehicle Modelling

This paper outlines the aerodynamics of the hypersonic waverider model which was designed by inviscid conical flowfield. Computational study was performed using method for splitting into physical processes which was implemented into UST3D computer code. The comparison between experimental data and calculations is presented. Assuming that flow about waverider is turbulent the effects of viscous interaction are taken into account by reference temperature method. Calculations were conducted using unstructured tetrahedron mesh

References

[1] Zheleznyakova A.L., Surzhikov S.T. Na puti k sozdaniyu virtualnoy modeli GLA. I [On the way to creation of hypersonic HCV virtual model. I]. Moscow, IPMekh RAN Publ., 2013. 160 p.

[2] Nonweiler T.R.F. Aerodynamic problems of manned space vehicle. The Aeronautical Journal, 1959, vol. 63, no. 585, pp. 521–528.

[3] Corda S., Anderson J.D.Jr. Viscous optimized hypersonic waveriders designed from axisymmetric flow fields. AIAA 26th Aerospace Sciences Meeting, 1988, AIAA Paper 88–0369.

[4] Bowcutt K.G., Anderson J.D.Jr., Capriotti D.P. Viscous optimized hypersonic waveriders. AIAA 25th Aerospace Sciences Meeting, 1987, AIAA Paper 87–0272.

[5] Rasmussen M.L. Waverider configurations derived from inclined circular and elliptic cones. Journal of Spacecraft and Rockets, 1980, vol. 17, no. 6, pp. 537–545. 32 ISSN 0236-3941.

[6] Bauer S.X.S., Covell P.F., Forrest D.K., McGrath B.E. Preliminary assessment of a Mach 4 and a Mach 6 Waverider. Proc. of 1st Int. Hypersonic Waverider Symp., University of Maryland, College Park MD, 1990, pp. 1–24.

[7] Cockrell Ch.E.Jr., Huebner L.D., Finley D.B. Aerodynamic characteristics of two waverider-derived hypersonic cruise configurations. NASA Technical Paper no. 3559, 1996. 78 p.

[8] Anderson J.D.Jr. Hypersonic and high temperature gas dynamics. New York, McGraw-Hill Book Company, 1989.

[9] Jones J.G., Woods B.A. The design of compression surfaces for high supersonic speeds using conical flow fields. London, Her Majestys Stationery Office, 1968. 25 p.

[10] Zheleznyakova A.L., Surzhikov S.T. Application of the method of splitting by physical processes for the computation of a hypersonic flow over an aircraft model of complex configuration. High Temperature, 2013, vol. 51, no. 6, pp. 816–829. DOI: 10.1134/S0018151X13050234

[11] Surzhikov S.T. Validation of computational code UST3D by the example of experimental aerodynamic data. Journal of Physics: Conference Series, 2017, vol. 815, no. 1, paper 012004. DOI: 10.1088/1742-6596/815/1/012005 Available at: http://iopscience.iop.org/article/10.1088/1742-6596/815/1/012005

[12] Marchuk G.I. Metody rasshchepleniya [Distribution methods]. Moscow, Nauka Publ., 1988. 263 p.

[13] Belotserkovskiy O.M., Davydov Yu.M. Metod krupnykh chastits v gazovoy dinamike [Large particle methods in gas dynamics]. Moscow, Nauka Publ., 1982. 392 p.

[14] Cockrell Ch.E.Jr. Vehicle integration effects on hypersonic waveriders. M.S. thesis. George Washington University, 1994. 132 p.

[15] Takashima N., Lewis M. Navier — Stokes computation of a viscous optimized waverider. Journal of Spacecraft and Rockets, 1994, vol. 31, no. 3, pp. 383–391.

[16] Dilley A.D. Evaluation of CFD turbulent heating prediction techniques and comparison with hypersonic experimental data. NASA/CR-2001-210837. NASA, 2001. 31 p.