Document Type : Scientific extension


1 M. Sc., School of Mechanical Engineering, College of Engineering, University of Tehran ، Tehran، Iran

2 PhD, Space Transportation Research Institute, Iranian Space Research Center، Tehran، Iran


In the present research about 50 high altitude test facilities (HATFs) in the world and ejectors of them have been analyzed. Practical information such as type of the ejector, operating fluid, procedure of fluid generation, operating pressure and temperature, Thermal protection and costs of construction and operation can be useful in developing space industries. The present study shows that in 87% of the 50 HATFs, central ejectors and in 76% of them water steam have been used. Water spray cooling is often used to provide thermal protection for ejectors. Based on the available references, the water mass flow rate for cooling system is in the range of 1.8 to 3.9 times of the mass flow rate of exhaust gases of the engines with thrust in the range of 0.11 to 204 kN. To produce water steam, the HATFs for solid and liquid fuel engines frequently employ the steam accumulators and steam generators, respectively.


[1]  Ducasse, P. “Rocket Altitude Test Facilities Register,”AdvistoryGroup for Aerospace Research and Development Neuilly-Sur-Seine (FRANCE(, North Atlantic Treaty Organization Advisory Group for Aerospace Research and Development, AGARDograph No. 297, 1987.
[2]  Aidoun, Z. and Ouzzane, M., “The Effect of Operating Conditions on the Performance of a Supersonic Ejector for Refrigeration”, International Journal of Refrigeration, Vol. 27, No. 8, 2004, pp. 974-984.
[3]  Balamurugan, S., Lad, M. D., Gaikar, V. G. and Patwardhan, A. W., “Hydrodynamics and Mass Transfer Characteristics of Gas–Liquid Ejectors”, Chemical Engineering Journal, Vol. 131, No. 1, 2007, pp. 83-103.
[4]  Zhu, Y., Li, Y. and Cai, W., “Control Oriented Modeling of Ejector in Anode Gas Recirculation Solid Oxygen Fuel Cell Systems”, Energy Conversion and Management, Vol. 52, No. 4, 2011, pp. 1881-1889.
[5]  Kumaran, M.R., Vivekanand, P.K. and Sundararajan, T., “Optimization of Second Throat Ejectors for High-Altitude Test Facility”, Journal of Propulsion and Power, Vol. 25, No. 3, 2009, pp. 697-706.
[6]  [6] Kim, S. and Kwon, S., “Experimental Determination of Geometric Parameters for an Annular Injection Type Supersonic Ejector”, Journal of Fluids Engineering, Vol. 128, No. 6,2006, pp. 1164-1171.
[7]  Bruce Ralphin, R.J. and Brindha, C., “Investigation on the Feasibility of High Altitude Testing Facility for Flow Analysis” ,International Journal of Innovation in Science and Mathematics, Vol. 2, 2014, ISSN 2347-9051.
[8]  Sathiyamoorthy, K., Iyengar, V.S. and Manjunath, P., “Annular Supersonic Ejector Design and Optimization”, American Society of MechanicalEngineersin ASME 2012 Gas Turbine India Conference, 2012.
[9]  Chen, J., Wu, J., Wang, Z. and Lue, W., “The Effect of Secondary Flows on the Starting Pressure for a Second-Throat Supersonic Ejector”, Journal of Thermal Science, Vol. 20, No6, 2011, pp. 503-509.
[10]  Sun, D.W. and Eames, I.W., “Recent Developments in the Design Theories and Application of Ejectors: a Review”, Journal of the Institute of Energy, Vol. 68, No. 475, 1995, pp. 65-79.
[11]  Park, G., Kim, S. and Kwon, S., “A Starting Procedure of Supersonic Ejector to Minimize Primary Pressure Load”.Journal of Propulsion and Power, Vol. 24, No. 3, 2008, pp. 631-634.
[12]  Karthick, S.,Srisha, M.V.R., Jagadeesh, G. and Reddy, K.P.J., “Parametric Experimental Studies on Mixing Characteristics within a Low Area Ratio Rectangular Supersonic Gaseous Ejector”,Physics of Fluids, Vol. 28, No. 7, 2016, pp. 1-26.
[13]  Kim, S. and Kwon, S., “Starting Pressure and Hysteresis Behavior of an Annular Injection Supersonic Ejector”,AIAA Journal, Vol. 46, No. 5, 2008, pp. 1039-1044.
[14]  Kanda, T., Ogawa, Y.,Sugimori, D. and Kojima, M., “Conceptual Design Model of High-Altitude Test Stand for Rocket Engines”Tranactions of the Japan Society for Aeronautical and Space Science, Vol. 59, No. 3, 2016,            pp. 161–169.
[15]  Kumaran, R.M., Sundararajan, T., Manohar, D.R. and Dason, D., “Modeling of Two-Stage Ejector for High-Altitude Testing of Satellite Thrusters”, AIAA Journal, Vol. 50, No. 6, 2012, pp. 1398-1408.
[16]  Kumaran, R.M., Sundararajan, T. and Manohar, D.R., “Simulations of High Altitude Tests for Large Area Ratio Rocket Motors”, AIAA Journal, Vol. 51, No. 2, 2013,pp. 433-443.
[17]  Bruce Ralphin, R.J. and Vijin, C., “Optimization of Supersonic Ejector by Condensing Rocket Plume”, American Journal of Science and Technology, Vol. 2, No. 4, 2015,pp. 116-123.
[18]  Rao, B.N. and Reddy, K.V., “Performance of Cooling Hot Gas Discharge Spray Cooler with Flow Parameters Variation”Indian Journal of Science and Technology, Vol. 5, No. 5, 2012,pp. 2762-2764.
[19]  Rajagopal, M. and Rajamanohar, D., “Modeling of an Exhaust Gas Cooler in a High-Altitude Test Facility of Large-Area Ratio Rocket Engines”,Journal of Aerospace Engineering, Vol. 28, No. 1, 2014, pp. 04014049(1)- 04014049(9).
[20]  Kubiak J.M. and Arnett, L.A., “Green Propellant Test Capabilities of the Altitude Combustion Stand at the NASA Glenn Research Center”, National Aeronautics and Space Administration, Cleveland, Ohio, 2017.
[21]  Margetts, M.J. and Geery, E.L., “Water Injection for Rapid Cooling of a Flow of Rocket Exhaust Gases”, AIAA5th Propulsion Joint Specialist Conference, No. 69-514, 1969.
[22]  Goethert, B., “High Altitude andSpace Simulation Testing”.ARS Journal, Vol. 32, No. 6, 1962,pp. 872-882.
[23]  Reinkenhof, J. and Schmucker, R.H., “H2/O2 Rocket Engine Steam Generator for Future Power Plants,” Journal of Energy, Vol. 2, No. 2, 1978, pp. 100-105.
[24] Carman, C.T., “Development of a Gas Generator Using a Rocket-Type Combustor as the Heat Source,” Arnold Engineering Development Center, Air Force Systems Command, United States Air Force, ARO Project No. 106045, Project 6950, 1962.
[25]  Heil, M., “Rocket Testing at AEDC”, Report by NASA, Arnold Engineering Development Center, United State of America, 2017.
[26]  Schäfer, K., Zimmermann, H. and Kruhsel, G., “Altitude Simulation Bench for VINCI Engine”, in 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2003.
[27] Solfanelli, G., Rose, L.D. and Porcu, E., “A New Simulated Altitude Facility for Space Motor Tests”, in 18thAIAA/SAE/ASME Joint Propulsion Conference, 1982.
[28] Beisler, M., “J-3 Test Stand”, National Rocket Propulsion Test Alliance (N.R.P.T), SDC Operations , Vol. 228, 688-2525 Option 3, Alliance, Editor, 2017.
[29] Beisler, M., “J-4 Cutaway”, National Rocket Propulsion Test Alliance (N.R.P.T), SDC Operations (228) 688-2525 Option 3, Alliance, Editor, 2017.
[30] Roux, J. and McCay, T., “Spacecraft Contamination: Sources and Prevention”, American Institute of Aeronautics and Astronautics, Vol. 91, 1984.
[31] Beisler, M., “J-5 Test stand”, National Rocket Propulsion Test Alliance (N.R.P.T), SDC Operations (228) 688-2525 Option 3, Alliance, Editor, 2017.
[32]  Dunham, J.R., “J-6 Large Rocket Motor Test Facility”, Arnold Air Force Base, Editor, 2013.
[33]  Lyndon, B., “Propulsion 400 Area Large Altitude Simulation System”, National Aeronautics and Space Administration, White Sands Test Facility, 2017.
[34]  Mills, A.K. andArrighi, R.S., “B–1 and B–3 Test Stands”, NASA Glenn Research Center Report, 21000 Brookpark Road, Cleveland, OH 44135, 2010.
[35]  Kudlac, M., Weaver, H. and Cmar, M., “NASA Plum Brook's B-2 test Facility-Thermal vacuum and propellant test facility”, American Institute of physics, NASA Glenn Research Center, 2012.
[36]  Arrington, L. and Schneider, S., “Low thrust rocket test facility”, 26th Joint Propulsion Conferencecosponsored by the MAA, SAE, ASME, and ASEE, NASA Technical Memorandum 103206, 1990.
[37]  Mitsubishi Heavy Industries Group, “High-altitude Performance Test Facility”, Japanese High - Altitude Test Facilities, 2015.
[38]  White Sands Tests, “White Sands Test Facility Propulsion Test Stands”, Report by NASA, 2017.
[39]  Beisler, M., “J-6 Test Stand”, National Rocket Propulsion Test Alliance (N.R.P.T), SDC Operations (228) 688-2525 Option 3, Alliance, Editor, 2017.
[40]  Beisler, M., “J-2A Test Stand”, National Rocket Propulsion Test Alliance (N.R.P.T), SDC Operations (228) 688-2525 Option 3, Alliance, Editor, 2017.
[41]  Beisler, M., “Spacecraft Propulsion Test Facility (B-2)”, National Rocket Propulsion Test Alliance (N.R.P.T), SDC Operations (228) 688-2525 Option 3, Alliance, Editor, 2017.
[42]  Lewis, G.E. and Drabble, J.S., “Ejector Experiments” NGTE R-151, National Gas Turbine Establishment, 1954.