Further Experiments on an NACA 23021 Aerofoil with a 15 per cent Handley Page Slotted Flap in the Compressed Air Tunnel

摘要

The NACA 23021 aerofoil was tested with a form of flap and slot which was a modification of the form tested as described in R. & M. 2305. The main modification was a rounding-off of the trailing edge of the main wing on the lower surface and of the leading edge of the flap, thus making the gap on the lower surface appreciably larger.nThe results are very similar to those obtained on the earlier model. Cimz after increasing with flap angle up to a flap angle of 60 deg shows a definite decrease at 80 deg. There appear to be two values possible at 70 deg the results in the one case being similar to those at 60 deg and in the other, bearing more resemblance to the results at 80 deg.nAn overall check of apparatus and model was obtained by closing the gap at 60 deg flap angle, and repeating with satisfactory results some of the tests on the original model.