Hostname: page-component-586b7cd67f-g8jcs Total loading time: 0 Render date: 2024-11-24T15:28:48.507Z Has data issue: false hasContentIssue false
  • English
  • Français

A Comparison of Two Prediction Methods with Experiment for Compressible Turbulent Boundary Layers with Air Injection

Published online by Cambridge University Press:  07 June 2016

G D Thomas ,
V K Verma  and
L C Squire
G D Thomas
Affiliation:
Cambridge University, Engineering Department
V K Verma
Affiliation:
Cambridge University, Engineering Department
L C Squire
Affiliation:
Cambridge University, Engineering Department
Get access

Summary

Two prediction methods for compressible turbulent boundary layers with air injection have been developed. The results from the two methods are compared with experiment for constant pressure flows at Mach numbers from 1.8 to 3.6. In general the results from the two methods and from experiment are in close agreement. However, there are some differences at the higher Mach numbers and it is suggested that both methods need further development for use at Mach numbers above 3.

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 4 , November 1972 , pp. 301 - 306
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. Bradshaw, P Ferriss, D H Atwell, N P Calculation of boundary-layer development using the turbulence energy equation. Journal of Fluid Mechanics, Vol 28, pp 593-616, 1967.Google Scholar
2. Bradshaw, P Ferriss, D H Calculation of boundary-layer development using the turbulence energy equation: compressible flow on adiabatic walls. Journal of Fluid Mechanics, Vol 46, pp 83-110, 1971.Google Scholar
3. Cebeci, T A finite-difference method for calculating compressible laminar and turbulent AMO Smith boundary layers. Journal of Basic Engineering (ASME), Vol 92, pp 523–535, 1970.Google Scholar
4. Squire, L C Further experimental investigations of compressible turbulent boundary layers with air injection. ARC R&M 3627, 1970.Google Scholar
5. Jeromin, L O F An experimental investigation of the compressible turbulent boundary layer with air injection. ARC R&M 3526, 1968.CrossRefGoogle Scholar
6. Cebeci, T Calculation of compressible turbulent boundary layers with heat and mass transfer. AIAA Journal, Vol 9, pp 1091-1097, 1971.Google Scholar
7. Coles, D Measurements in the boundary layer on a smooth flat plate in supersonic flow. Jet Propulsion Laboratory, Report 20-69, 1953.Google Scholar
8. Rubesin, M W Maydew, R C Varga, S A An analytical and experimental investigation of skin friction of the turbulent boundary layer on a flat plate at supersonic speeds. NACA TN 2305, 1951.Google Scholar
9. Winter, K G Gaudet, L Some recent work on compressible turbulent boundary layers and excrescence drag. Paper 15 in NASA SP-216, 1968.Google Scholar
10. Adcock, J B Petersen, J B McRee, J Experimental investigation of a turbulent boundary layer at Mach 6, high Reynolds number and zero heat transfer. NASA TN D 3882, 1967.Google Scholar
11. Spalding, D B Chi, S W The drag of a compressible turbulent boundary layer on a smooth flat plate with and without heat transfer. Journal of Fluid Mechanics, Vol 18, pp 117–143, 1964.Google Scholar
12. Squire, L C A law of the wall for compressible turbulent boundary layers with air injection. Journal of Fluid Mechanics, Vol 37, pp 449-456, 1969.CrossRefGoogle Scholar
13. Verma, V K A method of calculation for two-dimensional and axisymmetric boundary layers. Cambridge University Engineering Department, CUED/A-Aero/TR3, 1971.Google Scholar