Abstract:
A series of tests on an 8.6 per cent thick nose-suction aerofoil designed by Lighthill has been made in the 4 ft No. 2 Wind Tunnel at the National Physical Laboratory at Reynolds numbers of 0.385 and 0.577 x 10(to the power of 6). The results show that the wing stalls at alpha ~= 3 deg (Cl = 1.12) without suction, the lift coefficient at the stall increasing approximately linearly with suction quantity and reaching 1.93 at Cq = 0.019 and 23 deg incidence.