The possibility of reducing the base drag of the blunt trailing edges on Concorde by a method of castellating the trailing edges was examined. It is concluded that castellations produce a 30 % decrease in the base drag but that the same improvement may be achieved from a uniform extension along the whole span of the wing. The investigation was carried out with a value of boundary layer momentum thickness to base height much less than that on Concorde. It is suggested that reductions in base pressures obtained in flight tests are due to effects known to occur with castellations at subsonic velocities rather than any unknown mechanism at supersonic velocities. (Author)
An Investigation into the Effect of Castellating a Blunt Trailing Edge in Supersonic Flow
1974
38 pages
Report
No indication
English
Blunt Trailing Edge Cooling Effects at Supersonic Regime
AIAA | 2009
|Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities
Engineering Index Backfile | 1952
|