Abstract
SummaryExperiments were made on an aerofoil of 25 per cent, thickness with a suction slot at the rear and a flap that could be withdrawn into the slot. The main object of the work was to investigate the effect of withdrawing the flap when all the air in the boundary layer was sucked into the slot. In particular, as a test of the type of anti-gust device proposed by Thwaites, it was required to observe the change of lift that occurred during withdrawal of the flap and a subsequent change of incidence (with the flap still withdrawn).The flow was investigated by the use of smoke and tufts, by pressure plotting on the surface of the aerofoil, and by measurements of total and static pressures in the wake. The effects of varying incidence, flap position, and suction velocity were investigated.It was found that the provision of a flap downstream of the enclosing streamline, so that the rear stagnation point was not in the free fluid, was all important in relation to the behaviour of an aerofoil which had a suction slot at its rounded rear.With the flap extended beyond the enclosing streamline and with the ratio of suction-slot velocity to free stream velocity higher than the theoretical value, a stable flow was obtained within the theoretical incidence range. A favourable pressure gradient was observed in the slot entry and no measureable wake existed downstream of the flap. Smoke filaments, emitted from a tube projecting from the slot slightly beyond the enclosing streamline, travelled far downstream with apparently little diffusion.When the flap was placed so that its trailing edge was inside the enclosing streamline, i.e. so that there was in theory a stagnation point in the free fluid, an instability of a three-dimensional character occurred, with a wide wake and a large drag coefficient. The lift curves were unusual and it was found that movement of the flap caused a large change of lift coefficient. There was no evidence that the lift could be maintained constant, independent of incidence, when the flap was withdrawn into the slot.
Publisher
Cambridge University Press (CUP)
Reference18 articles.
1. Pfenninger W. (1947). Investigations on Reductions of Friction on Wings, in particular by means of Boundary Layer Suction. N.A.C.A. T.M. 1181.
2. Lighthill M. J. (1945). A New Method of Two-Dimensional Aerodynamic Design. R. & M. 2112, April 1945.
3. Gregory N. , Pankhurst R. C. and Walker W. S. (1950). Wind Tunnel Tests on the Prevention of Boundary Layer Separation by Distributed Suction at the Rear of a Thick Aerofoil. A.R.C. 13,446.
4. Melvill Jones Sir (1936). Measurement of Profile Drag by the Pitot Traverse Method. R. & M. 1688.
5. NON-STEADY FLOWS UNDER ASYMPTOTIC SUCTION CONDITIONS
Cited by
7 articles.
订阅此论文施引文献
订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献