Aerodynamic Design of Mach 5 Nozzle in Large Hypersonic Wind Tunnel
Vandana Vidyadhari
PG Scholar, Aeronautical Engineering, Anna University, Tirunelveli
S Rajakumar
Assistant Professor, Mechanical Engineering, Anna University, Tirunelveli
23-31
Vol: 7, Issue: 3, 2017
Receiving Date:
2017-05-09
Acceptance Date:
2017-06-30
Publication Date:
2017-07-16
Download PDF
Abstract
The paper involves a design of Mach 5 Nozzle from an existing Mach 6 Nozzle of a large Hypersonic Wind Tunnel in Vikram Sarabhai Space Centre, Thiruvananthapuram in order to obtain the simulation of Mach 5. The work deals with design of nozzle contour using specific boundary conditions, where by changing minimum numbers of existing nozzle components. A new contour design can be arrived without sacrificing exit flow quality of the nozzle. Mach 6 nozzle is converted into Mach 5 nozzle by changing 3 nos. of segments viz. convergent, throat and 1st divergent segment in order to reduce cost of design, installation and manufacturing. Axisymmetric CFD flow analysis of Mach 5 contour is done in Fluent to confirm the flow uniformity at the nozzle exit. Different contours are generated by varying the throat location and radius of curvature of throat. The flow simulation carried out using CFD for the different contours in order to obtain the best flow quality at the nozzle exit.
Keywords:
axisymmetric nozzle; contour; flow uniformity; flow quality; grid sensitivity analysis
References
- Ying-Nien Yu, NATO AGARDograph, “A Summary of Design techniques for Axisymmetric Hypersonic Wind Tunnels”.
- James C. Sivells, Journal of Spacecrafts and Rockets, Vol. 7, No. 11, “Aerodynamic design of Axisymmetric Hypersonic Wind Tunnel Nozzles”.
- Richard L Gaffney Jr., Brian K. Stewart, Stephen F. Harwin, 25th AIAA Aerodynamic Measurement Technology and Ground testing Conference, June 2006, “Design of a High Q Mach 5 Nozzle for the NASA Langley 8Ft HTT”.
- Tharen Rice, John Hopkins University, Applied Physics Laboratory, June, 2003,“2D and 3D method of characteristics tool for complex nozzle development”.
- D. F. Long and G. J. Hanust, AIAA-0044, “Aerodynamic design and Analysis of a Dual throat Hypersonic Nozzle”.
- R. Sauer, NACA (National Advisory Committee for Aeronautics), Technical Memorandum No.1133, “Method of Characteristics of 3D-Axially symmetric supersonic flows”.
- B.KrishnaPrafulla, V.ChittiBabu and P.GovindaRao, International Journal of Computational Engineering Research, Vol 03, Issue 5, May 2013,“CFD Analysis of Convergent-Divergent Supersonic Nozzle”.
- Cronvich.LL, Journal of Aeronautical Sciences, Vol 15,No.3, “A Numerical-Graphical Method of Characteristics for axially symmetric Isentropic flow”.
- Kevin L.Mikkelsen and D.F.Long, 43rdAIAA Aerospace Sciences Meeting and Exhibit, Jan 2005, “Refurbishment,Calibration and Initial testing in the ASE Hypersonic Wind Tunnel”.
- Kenney JT, Webb LM, AGARDograph3, “A Summary of techniques of Variable Mach Number Supersonic Wind Tunnel Nozzle design”.
- H.LewisFlight Propulsion Laboratory, Cleaveland, Ohio, “Internal performance characteristics of a short convergent-divergent exhaust nozzle designed by method of characteristics”.
- Pu Zhang, JingleiXu, ZhibinQuan, Jianwei Mo, ActaAstronautica, September 2016,“Effects of Nonuniform Mach-number Entrance on Scramjet Nozzle Flowfield and Performance”.
- Olivera P. Kostic, Zoran A. Stefanovic, Ivan A. Kostic, FME transactions, 2015, “CFD modeling of supersonic airflow generated by 2D nozzle with and without an obstacle at the exit section”
- GUO Shan-guang, WANG Zhen-guo, ZHAO Yu-xin, Science and Technology on Scramjet Laboratory, 2015, “Design of a continuously variable Mach-number nozzle”.
- S.M.Aulchenko, V.M.Galkin, V.I.Zvegintsev, A.N.Shiplyuk, International Conference on Methods of Aerophysical Research, ICMAR 2008, “Design of a multimode axisymmetric nozzle for a hypersonic wind tunnel by methods of numerical optimization”.
- H. Wei, W. Y.K. Chan, P. A. Jacobs, and R. G. Morgan, 19th Australasian Fluid Mechanics Conference, December 2014 , “Computational Optimisation and Analysis of A Truncated Hypersonic Nozzle for X3 Expansion Tunnel”.
Back
