Skip to main content
SpringerLink
Log in

Axisymmetric Inlet Flow at Low Supersonic Mach Numbers

  • Conference paper
Symposium Transsonicum II

  • 186 Accesses

Summary

A calculation method for transonic flow around axisymmetric inlets in subsonic free streams has been extended to work in supersonic free streams. The full potential equation is solved in non-conservative and almost conservative (quasi-conservative) form using line-relaxation.

In a comparison with experiments the non-conservative and quasiconservative formulation give shock wave locations somewhat upstream and downstream respectively of the experimental shock wave.

This is a preview of subscription content, log in via an institution to check access.

Access this chapter

Log in via an institution
Chapter
USD 29.95
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
eBook
USD 84.99
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
Softcover Book
USD 109.99
Price excludes VAT (USA)
  • Compact, lightweight edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info

Tax calculation will be finalised at checkout

Purchases are for personal use only

Institutional subscriptions

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. Colehour, J.L.: Transonic flow analysis using a stream-line coordinate transformation procedure. AIAA Paper 73-657, 1973.

    Google Scholar 

  2. Arlinger, B.G.: Calculation of transonic flow around axisymmetric inlets. AIAA Paper 75-80, 1975.

    Google Scholar 

  3. Jameson, A.: Transonic potential flow calculations using conservation form. 2nd AIAA Computational Fluid Dynamics Conf., Hartford, Conn. June 19–20, 1975.

    Google Scholar 

  4. Murman, E.M.: Analysis of embedded shock waves calculated by relaxation methods. AIAA J. May 1974 pp. 626-633.

    Google Scholar 

  5. Olstad, W.B.: Transonic-wind-tunnel investigation of the effects of lip bluntness and shape on the drag and pressure recovery of a normal-shock nose inlet in a body of revolution. NACA RM L56C28, 1956.

    Google Scholar 

Download references

Author information

Authors and Affiliations

  1. SAAB-SCANIA AB, Linköping, Sweden

    Bert G. Arlinger

Authors
  1. Bert G. Arlinger
    View author publications

    You can also search for this author in PubMed Google Scholar

Editor information

Editors and Affiliations

  1. Instituts für Strömungslehre, Technischen Hochschule Wien, Austria

    Klaus Oswatitsch (o. Professor und Vorstand) (o. Professor und Vorstand)

  2. Deutsche Forschungs- und Versuchsanstalt für Luft Raumfahrt e.V., Aerodynamische Versuchsanstalt, Göttingen, Germany

    Dietrich Rues (Priv. Doz.) (Priv. Doz.)

Rights and permissions

Reprints and permissions

Copyright information

© 1976 Springer-Verlag, Berlin/Heidelberg

About this paper

Cite this paper

Arlinger, B.G. (1976). Axisymmetric Inlet Flow at Low Supersonic Mach Numbers. In: Oswatitsch, K., Rues, D. (eds) Symposium Transsonicum II. International Union of Theoretical and Applied Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-81005-3_21

Download citation

  • DOI: https://doi.org/10.1007/978-3-642-81005-3_21

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-642-81007-7

  • Online ISBN: 978-3-642-81005-3

  • eBook Packages: Springer Book Archive

Publish with us

Policies and ethics

Search

Navigation