The profile drag of biconvex wing sections at supersonic speeds
The method detailed in a previous paper1 for calculating the profile drag of a wing section at supersonic speeds has been applied to a flat plate and two biconvex wing sections of thickness chord ratio 0.05 and 0.10 with zero heat transfer. Ranges of Mach number from 1.5 to 5.0, Reynolds number from 106 to 108 and transition position from the leading edge to the trailing edge have been covered, and the results are here presented in tabular and graphical form. It is found that with increase in Mach number, increase in thickness chord ratio and decrease in Reynolds number the effect of rearward movement of transition on skin friction and profile drag progressively decreases. The reasons for this are briefly discussed.
Unable to display preview. Download preview PDF.
- Young: The Calculation of the Profile Drag of Aerofoils and Bodies of Revolution at Supersonic Speeds. College of Aeronautics Report No. 73 (Apr. 1953).Google Scholar
- Wedderspoon and Young: Notes on the Results of some Profile Drag Calculations for a particular Body of Revolution at Supersonic Speeds. Conege of Aeronautics Report No. 81.Google Scholar
- Squire and Young: The Calculation of the Profile Drag of Aerofoils. A.R.C. R. and M. No. 1838 (1937).Google Scholar
- Young: The Calculation of the Total and Skin Friction Drags of Bodies of Revolution at Zero Incidence. A.R.C. R. and M. 1874 (1939).Google Scholar
- Young and Winterbottom: Note on the Effect of Compressibility on the Profile Drag of Aerofoils in the Absence of Shock Waves. A.R.C. R. and M. No. 2400 (1940).Google Scholar
- Young: Skin friction in the Laminar Boundary Layer in Compressible Flow. College of Aeronautics Report No. 20 (1948) also The Aeronautical Quarterly Vol. 1, Aug. 1949 p. 137–164.Google Scholar
- Crocco: Lo strato laminare. Monogr. Sci. Aeronautica 3 (1946).Google Scholar
- Cope: Notes and Graphs for Boundary Layer Calculations in Compressible Flow. A.R.C. Current Paper No. 89 (1951).Google Scholar
- Zienkiewicz: An Investigation of Boundary Layer Effects on Two Dimensional Supersonic Aerofoils. College of Aeronautics Report No. 49 (1951).Google Scholar
- Holder, Pearcey and Gadd: The Interaction between Shock Waves and Boundary Layers. A.R.C. Report No. 16, 526 (1954).Google Scholar