Hostname: page-component-586b7cd67f-t8hqh Total loading time: 0 Render date: 2024-11-24T22:30:32.538Z Has data issue: false hasContentIssue false
  • English
  • Français

A Shortened Method for the Calculation of Aerofoil Profile Drag*

Published online by Cambridge University Press:  28 July 2016

E. M. Dowlen
Get access Rights & Permissions [Opens in a new window]

Summary

A rapid method is developed for estimating the profile drag of an aerofoil with a known transition point position. The results are in good agreement with previous calculations.

Type
Research Article
Information
The Aeronautical Journal , Volume 56 , Issue 494 , February 1952 , pp. 109 - 116
Copyright
Copyright © Royal Aeronautical Society 1952

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.)

Footnotes

*

An extract from College of Aeronautics Report No. 35.

References

1. Squire, H. B. and Young, A. D. (1937). The Calculation of the Profile Drag of Aerofoils. R. & M. 1838, 1937.Google Scholar
2. Tetervin, Neal (1944). A Method for the Rapid Estimation of Turbulent Boundary Layer Thickness for Calculating Profile Drag. N.A.C.A. A.C.R. L4G14 (1944), A.R.C. 8498.Google Scholar
3. Young, A. D. (1948). Skin Friction in the Laminar Boundary Layer in Compressible Flow. College of Aeronautics Report No. 20, 1948.Google Scholar
4. Winterbottom, N. E. and Squire, H. B. (1940). Note on Further Wing Profile Drag Calculations. R.A.E. Report B.A. 1634, 1940.Google Scholar
5. Lock, R. C. (1948). Note on Profile Drag Calculations for Low-Drag Wings with Cusped Trailing Edges. R.A.E. Report Aero. 2130 and Corrigenda, 1948.Google Scholar