Abstract
The influence due to the shape of the expanding part of supersonic nozzles on the gas-dynamic structures formed in the ducts of high-altitude rocket and aerodynamic test benches has been studied. The research was carried out using the means of computational gas dynamics with the example of a model gas-dynamics tube with three replaceable supersonic nozzles having identical throat and outlet-section diameters. For confirming the adequacy of the models and methods used, the calculated values were compared to experimental ones. To this end, a model setup was developed, manufactured, and tested. Air with ambient temperature was used as the working medium. Another goal of the study was to compare the calculations performed with the use of different turbulence models.
Similar content being viewed by others
References
V.N. Berezhnoy, Activities in support of ground-base development testing of Liquid Rocket Engines (LRE) incorporating high-expansion ratio nozzles, Abstracts of the 14th International Conference “Aviation and Cosmonautics — 2015”, 2015, Moscow, MAI, 2015. P. 99–100.
P. Pempie and H. Vernin, Liquid rocket engine test plan comparison, in: 37th Joint Propulsion Conference and Exhibition, AIAA Paper, 2001, No. 2001-3256.
J.R. Bullock, M. Popp, and J. Santiago, Program status of the pratt & whitney RL60 engine, in: 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibition, AIAA Paper, 2002, No. 2002-3587.
J. Steelant, M. Marini, G. Pezella, B. Reimann, S.L. Chernyshev, A.A. Gubanov, V.A. Talyzin, N.V. Voevodenko, N.V. Kukshinov, A.N. Prokhorov, A.J. Neely, C. Kenell, D. Verstraete, and D. Buttsworth, Numerical and experimental research on the aerodynamics of high-speed passenger vehicle within the HEXAFLY-INT project, in: Proc. of the 30th Congress of the Inter. Council of the Aeronautical Sci., Daejeon, 2016, ICAS2016-0353, 2016.
V.Yu. Aleksandrov, N.V. Kukshinov, A.N. Prokhorov, and A.V. Rudinskiy, Analysis of the integral characterristics of HEXAFLY-INT facility module, in: Proc. of the 21th Inter. Space Planes and Hypersonic Systems and Technology Conf., Xiamen, 2017, AIAA Paper, 2017, No. 2017-2179.
A.M. Kharitonov, Techniques and Methods of Aerophysical Experiment, Pt. 1, Aerodynamic tubes and gas-dynamic facilities, NSTU Publ., Novosibirsk, 2005.
A. Pope and K.L. Goin, High-Speed Wing Tunnel Testing, John Wiley & Sons, London, 1965.
A.A. Shishkov and B.M. Silin, Jet Engine High-Altitude Tests. Mashinostroenie, Moscow, 1985.
G.G. Chernyi, Gas Dynamics, Nauka, Moscow, 1988.
C.L. Chen, S.R. Chakravarthy, and C.M. Hung, Numerical investigation of separated nozzle flows, AIAA J., 1994, Vol. 32, No. 9, P. 1836–1843.
M. Frey and G. Hagemann, Restricted shock separation in rocket nozzles, J. Propulsion and Power, 2000, Vol. 16, No. 3, P. 478–484.
M.S. Liou and C.J. Steffen, A new flux splitting scheme, J. Comput. Phys., 1993, Vol. 107, No. 1, P. 23–39.
P. Spalart and S. Allmaras, A one-equation turbulence model for aerodynamic flows, Technical Report AIAA-92-0439, 1992.
D.C. Wilcox, Turbulence Modeling for CFD, Inc. La Canada, California: DCW Industries, 1998.
F.R. Menter, Zonal two equation k-εturbulence models for aerodynamic flows, AIAA Paper, 1993, No. 93-2906.
F.R. Menter, Two-equation eddy-viscosity turbulence models for engng applications, AIAA J., 1994, Vol. 2, No. 8, P. 1598–1605.
I.A. Belov and S.A. Isaev, Modeling of Turbulent Flows, Study guide, St. Petersburg, Baltic State Technical University, 2001.
T.-H. Shih, W.W. Liou, A. Shabbir, Z. Yang, and J. Zhu, A new k-ε eddy-viscosity model for high Reynolds number turbulent flows — model development and validation, Computers Fluids, 1995, Vol. 24, No. 3, P. 227–238.
B.E. Launder and D.B. Spalding, The numerical computation of turbulent flows, Computer Methods in Applied Mechanics and Engng, 1974, No. 3. P. 269-289.
Yu.P. Gounko and I.N. Kavun, Unsteady pseudo-jump in a shock tube, J. Appl. Mech. Techn. Phys., 2020, Vol. 61, No. 2, P. 217–224.
Yu.P. Gounko and I.N. Kavun, Peculiarities of the flows forming in processes of an impulse starting of a supersonic wind tunnel with different diffusers, Thermophysics and Aeromechanics, 2019, Vol. 26, No. 2, P. 192–214.
Yu.P. Gounko and I.I. Mazhul, Flow turbulization in a pseudo-jump formed in an axisymmmetric channel duct with a frontal inlet, Thermophysics and Aeromechanics, 2018, Vol. 25, No. 3, P. 347–358.
A.A. Ponomarev and N.B. Ponomarev, About supersonic nozzle flow separation, Aerospace MAI J., 2011, Vol. 18, No. 3, P. 55–64.
A.A. Ponomarev, Experimental and numerical study of the appearance of the non-typical separation of nozzle flow and the loss of thrust density impulse due to the irregular composition of exhaust products, Dissertation for the Candidate Degree in Phys. and Math. Sciences, MAI Publ., Moscow, 2011.
Author information
Authors and Affiliations
Corresponding authors
Rights and permissions
About this article
Cite this article
Zakharov, V.S., Guskov, O.V., Prokhorov, A.N. et al. Computational and experimental study of the influence of the shape of nozzle supersonic part on the flow structure in the gas-dynamic flow path of a model high-altitude test facility. Thermophys. Aeromech. 28, 153–173 (2021). https://doi.org/10.1134/S0869864321020013
Received:
Revised:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1134/S0869864321020013