Hostname: page-component-7479d7b7d-k7p5g Total loading time: 0 Render date: 2024-07-13T15:48:26.484Z Has data issue: false hasContentIssue false
  • English
  • Français

Stagnation pressure effect on the supersonic minimum length nozzle design

Published online by Cambridge University Press:  19 June 2019

T. Zebbiche
T. Zebbiche*
Affiliation:
Institute of Aeronautics and Space Studies University of Blida 1Blida, Algeria
*
z_toufik270169@yahoo.fr
Get access Rights & Permissions [Opens in a new window]

Abstract

The aim of this work is to develop a calculation model based on the method of characteristics making it possible to study the effect of the stagnation pressure of the combustion chamber on the 2D and axisymmetric minimum length nozzle design giving a uniform and parallel flow at the exit section. The model is based on the use of the real gas approach. The co-volume and the intermolecular interaction effect are taken into account by the use of the Berthelot state equation. The effect of molecular vibration is considered in our model to evaluate the behaviour of gas at a high temperature. In this case, the stagnation pressure and the stagnation temperature are important parameters in our model. The resolution of the algebraic equations is done by the finite difference corrector predictor algorithm. The validation of the results is controlled by the convergence of the critical section ratios calculated numerically as obtained by the theory. The mass and the thrust are evaluated to improve the efficiency of the nozzle. The comparison is made with the high temperature and perfect gas models. The application is made for air.

Keywords

Minimum length nozzleStagnation temperatureStagnation pressureMethod of characteristicsReal gasBerthelot state equationHigh temperature modelPerfect gas modelReal gas modelThermodynamic ratiosTrustMassPredictor corrector algorithm
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1265 , July 2019 , pp. 1013 - 1031
Copyright
© Royal Aeronautical Society 2019 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

Peterson, C.R. and Hill, P.G. Mechanics and Thermodynamics of Propulsion, Addition-Wesley Publishing Company, 1965, New York, US.Google Scholar
Sutton, G.P. and Biblarz, O. Rocket Propulsion Elements, 8th ed., John Wiley and Sons, US, 2010.Google Scholar
Emanuel, G. and Argrow, B.M. Comparison of minimum length nozzles, J Fluid Engineering, Transaction of ASME, 1998, 110, pp 283–288.Google Scholar
Ostlund, J., Damgaad, T. and Frey, M. Side-load phenomena in highly over-expanded rocket nozzle, J Propulsion and Power, 2004, 20, (4), pp 695–704.Google Scholar
Papamoschou, D. and Zill, A. Fundamental investigation of supersonic nozzle flow separation, AIAA J, 2004, 42, (08), pp 1101–1111.Google Scholar
Ralf, H. and Chloe, G. Experimental study on rocket nozzle side load reduction, J Propulsion and Power, 2011, 28, (02), pp 307–311.Google Scholar
Ralf, H. and Chloe, G. Optimization of a rocket nozzle side load reduction device, J Propulsion and Power, 2016, 32, (06), pp 1395–1402.Google Scholar
Abada, O., Zebbiche, T. and Abdallah El-Hirtsi, A. Three-dimensional supersonic minimum length nozzle design at high temperature for arbitrary exit cross section, Arabian J Science and Engineering, 2014, 39, (11), pp 8233–8245.CrossRefGoogle Scholar
Zebbiche, T. Stagnation temperature effect on the supersonic axisymmetric minimum length nozzle design with application for air, Advances in Space Research, 2011, 48, pp 1656–1675.CrossRefGoogle Scholar
Zebbiche, T. and Youbi, Z. Supersonic two-dimensional minimum length nozzle design at high temperature. application for air, Chinese J Aeronautics, 2007, 20, (01), pp 29–39.Google Scholar
Zebbiche, T. and Youbi, Z. Effect of stagnation temperature on the supersonic flow parameters with application for air in nozzles, Aeronaut J, 2007, 111, (1115), pp 31–40.CrossRefGoogle Scholar
Zebbiche, T. Stagnation temperature effect on the Prandtl-Meyer function, AIAA J, 2007, 45, (04), pp 952–954.CrossRefGoogle Scholar
Zebbiche, T. and Boun-Jad, M. Numerical quadrature for the Prandtl-Meyer function at high temperature with application for air, Thermophysics and Aeromechanics, 2012, 19, (03), pp 381–384.CrossRefGoogle Scholar
Boun-Jad, M., Zebbiche, T. and Allali, A. Gas effect at high temperature on the supersonic nozzle conception, Int J Aeronautical and Space Sciences, 2017, 18, (01), pp 82–90.CrossRefGoogle Scholar
Boun-Jad, M., Zebbiche, T. and Allali, A. High temperature gas effect on the Prandtl-Meyer function with application for supersonic nozzle design, Mechanics and Industry, 2017, 18, (02), Article N° 219, Number of pages 9.CrossRefGoogle Scholar
Anderson, J. JR., Modern Compressible Flow: With Historical Perspective, McGrawHill, 1982, New York, US.Google Scholar
Thompson, A.P. Compressible Fluid Dynamics, McGraw-Hill, US, 1995.Google Scholar
Van Wylen, G.J. Fundamentals of Classical Thermodynamics, John Wiley and Sons, US, 1973.Google Scholar
Annamalai, K., Ishwar, K.P. and Milind, A.J. Advanced Thermodynamics Engineering, 2nd ed., CRC press, Taylor and Francis Group, 2011, US.Google Scholar
Salhi, M. and Zebbiche, T. Gaseous imperfections effect on the supersonic flow parameters for air in nozzles, 3rd International Conference and Exhibition on Mechanical & Aerospace Engineering, October 5–7, 2015, San Francisco, US.Google Scholar
Salhi, M., Zebbiche, T. and Mehalem, A. Stagnation pressure effect on Prandtl Meyer function for air, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2016, 231, (02), pp 326–337.CrossRefGoogle Scholar
Raltson, A. and Rabinowitz, A. A First Course in Numerical Analysis, McGraw-Hill, US, 1985.Google Scholar
Salhi, M., Zebbiche, T. and Roudane, M. Gaseous imperfections effects on the Prandtl Meyer Function with application for air, The International Conference on Engineering & Technology ICET’2017, August 21–23, 2017, Antalya, Turkey.Google Scholar
Salhi, M., Zebbiche, T. and Mehalem, A. Stagnation pressure effect on the supersonic flow parameters with application for air in nozzles, Aeronaut J, 2016, 120, (1224), pp 313–354.CrossRefGoogle Scholar
Nag, P.K. Engineering Thermodynamics, 4th ed., McGraw-Hill, 2008, New Delhi, India.Google Scholar