The induced drag factor of highly swept delta wing at subsonic speeds
Entry/Object ID
3416
Category
Report - Technical
Archive Items Details
Description
The induced drag factor for delta wings with approximately 60 degrees of leading edge sweepback is found to be affected greatly by the aerofoil section shape. For thin sections (e.g. 5 percent) or thick sections with sharp noses the induced drag factor varies between 0.40 and 0.50. For thick sections (e.g. 10 percent) values of 0.8 and 0.9 can be obtained. The above results apply for Reynolds' Numbers of 4 million or greater. On the basis of limited data it appears that the induced drag factor for thin sectioned wings does not change over the subsonic Mach Number range.
