Yarusevych, S., Sullivan, P., and Kawall, J., "Airfoil boundary layer separation and control at low Reynolds numbers," Exp. Fluids, Vol. 38, 2005, pp. 545-547.S. Yarusevych, P. Sullivan, J. Kawall, Airfoil boundary layer separation and control at low Reynolds numbers, Exp. Fluids...
The performance of both devices as separation control actuators is tested on a high-lift airfoil system.The AC-DBD is effective for controlling turbulent boundary layer separation from a deflected trailing edge flap between Reynolds numbers... Little, Jesse C. 被引量: 24发表: 2010年 A thermograp...
Turbulent at RN = 3 to the power of 6 ? 5. Boundary layer separation for such airfoil is developed gradually with increase of angle of attack or happen instantly just after the angle of attack reach the maximum ? Please help. Thank you ...
Supercritical airfoils feature four main benefits: they have a higher drag-divergence Mach number,[21] they develop shock waves farther aft than traditional airfoils,[22] they greatly reduce shock-induced boundary layer separation, and their geometry allows more efficient wing design (e.g., a thic...
flow separation at the LE with reattachment at a point which moves progressively rearward with increasing AOA. The role ofboundary-layer flowandseparation processesin relation tostallingas well asthe sensitivity of the stall to factorswhich influence boundary-layer growth, such as Reynolds number, is...
Then, an integral boundary layer method is applied, using a separate boundary layer analysis module. Beginning at the stagnation point, the method solves the boundary layer equations. According to information on the developer’s website, the equations and criteria for transition and separation were ...
(hard stall) abrupt flow separation near the leading edge (LE) without subsequent reattachment; the separation starts at theleading edgeof the aerofoil, the entire boundary layer may separate almost simultaneously thinairfoils, with thickness to chord ratio: 10- 16% (Figure 4.49, P389,Anserson,...
The most significant boundary layer phenomena such as laminar turbulent transition, laminar separation bubbles and boundary layer separation are considered. The first five chapters of this book describe in great detail a procedure for the design and analysis of subsonic airfoils. The data section ...
An exemplary use of the CFJ aircraft provides a method for reducing the boundary layer separation of an aerodynamic structure. The aerodynamic structure10may be operated such that a first mass of fluid is routed from the pressurized fluid source towards the injection opening. The first mass may ...
We propose a model which combines boundary layer computations with a free streamline potential flow for obtaining pressure distributions on an airfoil section in steady flow near stall conditions. The model is conceptually simple and uses elements which can be computed rapidly and efficiently. The solu...