Validation of computer code UST3D by the example of calculating the aerodynamic characteristics of the X–34 vehicle under various parameters
In the framework of the validation experiment conducted in this work, the aerodynamic characteristics of the X–34 vehicle were studied with variations in various angles of attack, Mach numbers, and model scales. The digital calculation was carried out using the computer code UST3D, developed in the laboratories of radiation gas dynamics of the IPMech RAS. This calculation module is designed for numerical integrated Navier-Stokes equations on tetrahedral unstructured grids. Based on the results of the work, satisfactory agreement was obtained on the nature of the flow and aerodynamic coefficient for models of different scaling, which are in reasonable agreement with the experiment.
flight simulation of the X–34 vehicle, various scales of the model, gas dynamics, validation experiment
В рамках валидационного эксперимента, проводимого в данной работе, были исследованы аэродинамические характеристики летательного аппарата Х–34 при вариации различных углов атаки, чисел Маха и масштабов модели. Численный расчет проводился с использованием компьютерного кода UST3D, разработанного в лаборатории радиационной газовой динамики ИПМех РАН. Данный расчетный модуль предназначен для численного интегрирования уравнений Навье-Стокса на тетраэдральных неструктурированных сетках. По итогам проведенной работы было продемонстрировано удовлетворительное согласие по характеру потока и аэродинамическим коэффициентам для моделей различных масштабов, которые находятся в разумном согласии с экспериментом.
моделирование полета аппарата Х–34, разномасштабные модели, газовая динамика, валидационный эксперимент.
1. Brauchmann, G.J.; X-34 Vehicle Aerodynamic Characteristics, Journal of Spacecraft and Rockets, Vol. 36, No. 2, 1999, pp. 229-239 2. McGhee, R. J., Beasley, W. D., and Foster, J. M: "Recent Modifications and Calibration of the Langley Low-Turbulence Pressure Tunnel," NASA TP-2328, 1984. 3. Capone, F. J., Bangert, L. S., Asbury, S. C., Mills, C. T., and Bare, E. A.: "The NASA Langley 16-Foot Transonic Tunnel," NASA TP-3521, September 1995. 4. Jackson, C. M., Corlett, W. A., and Monta, W. J.: "Description and Calibration of the Langley Unitary Plan Wind Tunnel," NASA TP-1905, November 1981. 5. Micol, J.M.: Hypersonic Aerodynamic/Aerothermodynamic Testing Capabilities at Langley Research Center: Aerothermodynamic Facilities Complex," AIAA paper 95-2107, 1995 6. Pamadi B.N., Brauckmann G.J., Ruth M.J., Fuhrmann H.D. Aerodynamic Characteristics, Database Development and Flight Simulation of the X-34 Vehicle // 38th Aerospace Sciences Meeting & Exhibit, 10–13 January 2000, Reno, NV. AIAA 2000-0900. 17 p. 7. Bandu N. Pamadi and Gregory J. Brauckmann Aerodynamic Characteristics and Development of the Aerodynamic Database of the X-34 Reusable Launch Vehicle // International Symposium on Atmospheric Reentry Vehicles and Systems, March 16-18, 1999 Arcachon, France 8. S. T. Surzhikov, “Validation of computational code UST3D by the example of experimental aerodynamic data”, 10th International Conference on Aerophysics and Physical Mechanics of Classical and Quantum Systems, Journal of Physics Conference Series, 815, eds. S. Surzhikov, D. Andrienko, Y. Babou, G. Colonna, A. Dikaljuk, M. Ermakov, I. Kryukov, Teodorovich, IOP Publishing Ltd, 2017, UNSP 012023 9. Berry, S. A., Horvath, T. J., Difulvio, M., Glass, C., & Merski, N. R. (1999). X-34 Experimental Aeroheating at Mach 6 and 10. Journal of Spacecraft and Rockets
