Three-dimensional turbulent boundary layer calculations for swept wings

Recent applications of advanced computational methods in the aerodynamic design of transport aircraft configurations

“…These include the co-ordinate system in which the solution is to be found, the means of representing the wing in this co-ordinate system, the governing boundary-layer equations, the means of specifying the initial and boundary conditions, the model chosen to represent the turbulent stresses present, and the numerical procedure used to generate the solutions. Numerous investigators' [5][6][7][8] ' using various combinations of approaches have tackled this problem with varying degrees of success. At Douglas, the work of Cebeci, Kaups and Ramsey (CKR) led to the development of a procedure for arbitrary wings' 51 which is unique in many aspects.…”

“…However, for as many examples as are presented showing good agreement between experiment and essentially inviscid computational methods, one can be sure that there are at least as many other examples where the agreement is poor due to the presence of strong viscous effects. To attack this problem, numerous organisations have been pursuing the coupling of various three-dimensional boundary-layer methods with three-dimensional transonic flow analysis methods' [5][6][7][8] '. The effort at Douglas on this problem has focused primarily on the use of a new, improved version of the Cebeci-Kaups-Ramsey (CKR) three-dimensional finite-difference boundary-layer program in conjunction with a Douglas version of the Jameson-Caughey full-potential program.…”

Efficient Transonic Shock-Free Wing Redesign Procedure Using a Fictitious Gas Method

“…The method is also extendable to wing design when it is combined with a threedimensional boundary-layer code. 21 The shock-free wing design method presented here tends to reduce the maximum thickness of the original wing. For flows at high freestream Mach numbers or at high lift coefficients, the thickness reduction invoked in the design process may in certain cases be too large to be acceptable.…”