Hostname: page-component-cd9895bd7-gxg78 Total loading time: 0 Render date: 2024-12-26T21:51:56.925Z Has data issue: false hasContentIssue false
  • English
  • Français

An Investigation into the Flow around a Family of Elliptically Nosed Cylinders at Zero Incidence at M∞ = 2.5 and M∞ = 4

Published online by Cambridge University Press:  07 June 2016

D R Philpott
D R Philpott*
Affiliation:
Department of Mechanical and Aeronautical Engineering, The Hatfield Polytechnic
Get access

Summary

Surface pressure measurements and schlieren photographs at M∞ = 2.50 and M∞ = 4.00 are presented for a family of axisymmetric elliptically-nosed models with cylindrical afterbodies. The results are an extension of those obtained by Holder and Chinneck on the same series of models at lower Mach numbers.

Some comparison is made with theoretical results, and the forebody surface pressures obtained experimentally are found to be in good agreement with results obtained using either the method of integral relations or the time-dependent method.

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 4 , November 1972 , pp. 315 - 326
Copyright
Copyright © Royal Aeronautical Society. 1972

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

1. Belotserkovskii, O M Flow past a circular cylinder with a detached shock wave. AVCO TM RAD – 9 – TM – 59 – 66, 1959.Google Scholar
2. Traugott, S C An approximate solution of the direct supersonic blunt-body problem for arbitrary axisymmetric shapes. Journal of the Aero/Space Sciences, Vol.27, p 361, May 1960.CrossRefGoogle Scholar
3. Moretti, G Abbett, M A time-dependent computational method for blunt-body flows. AIAA Journal, Vol 4, p 2136, December 1966.CrossRefGoogle Scholar
4. Pugh, P G Ward, L C Drag estimation for simple forebody shapes. NPL Aero Report 1304, October 1969.Google Scholar
5. Holder, D W Chinneck, A Observations of the flow past elliptically-nosed two-dimensional cylinders and bodies of revolution in supersonic airstreams. Aeronautical Quarterly, Vol IV, p 317, February 1954.CrossRefGoogle Scholar
6. Preston, N O et al Proposed 9″ × 8″ supersonic wind tunnel for Hatfield College of Technology. British Aircraft Corporation (Guided Weapons Division), 1964.Google Scholar
7. Pugh, P G Peto, J The effects of the presence of static holes on the measurement of static pressures on models at supersonic speeds. NPL Aero Report 1292, March 1969.Google Scholar
8. Baer, A L Pressure distribution on a hemisphere-cylinder at supersonic and hypersonic Mach numbers. Arnold Engineering Development Center, AEDC TN 61 – 96, 1961.CrossRefGoogle Scholar
9. Baer, A L External wave drag of bodies, (v) Blunt forebodies at zero incidence. Aerodynamics Data Sheet S.02.03.06, Engineering Sciences Data Unit, Royal Aeronautical Society, June 1954.Google Scholar
10. Kumar, S Private communication, 1969.Google Scholar
11. Albone, C Private communication, 1970.Google Scholar
12. Pugh, P G Ward, L C The estimation of zero-incidence forebody pressure drag coefficients of axisymmetric bodies from measured bow shock shapes. NPL Aero Report 1245, ARC 29 350, August 1967.Google Scholar
13. Kaattari, G A method for predicting shock shapes and pressure distributions for a wide variety of blunt bodies at zero angle of attack. NASA TN D04539, April 1968.Google Scholar
14. Van Dyke, M D Gordon, M D Supersonic flow past a family of blunt axisymmetric bodies. NASA Report R-1, 1959.Google Scholar