Add to ORKGA state-of-the-art finite difference boundary-layer program incorporated into the NYU Transonic Analysis Program is described. Some possible treatments for the trailing edge region were investigated. Findings indicate the trailing edge region, still within the scope of an iterative potential flow, boundary layer program, appears feasible
Two research programs are described which directly relate to the application of natural laminar flow...
Wind tunnel investigation of helicopter directional control in rearward flight in ground effec
A 3-D laminar and turbulent boundary-layer method is developed for compressible flow over swept wing...
An airfoil design program and a boundary layer analysis were developed. Boundary conditions were der...
The growing application of computational aerodynamics to nonlinear helicopter problems is outlined, ...
A new computer program is presented for calculating the quasi-steady transonic flow past a helicopte...
The input parameters are presented for a computer program which performs calculations for inviscid i...
The development of a potential-flow/boundary-layer method for calculating subsonic and transonic tur...
The growing application of computational aerodynamics to nonlinear rotorcraft problems is outlined, ...
Aerodynamic research relating to modern helicopters includes the study of three dimensional, unstead...
This report discusses progress made on NASA Cooperative Agreement NCC2-545, 'An Experimental Study o...
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1989.In...
Differential equations and boundary conditions for a rotor blade in forward flight, with subsonic or...
The results are reported of the research on the viscous interactions effects on transonic airfoil de...
The optimum design of the advancing helicopter rotor for high-speed forward flight always involves a...
Two research programs are described which directly relate to the application of natural laminar flow...
Wind tunnel investigation of helicopter directional control in rearward flight in ground effec
A 3-D laminar and turbulent boundary-layer method is developed for compressible flow over swept wing...
An airfoil design program and a boundary layer analysis were developed. Boundary conditions were der...
The growing application of computational aerodynamics to nonlinear helicopter problems is outlined, ...
A new computer program is presented for calculating the quasi-steady transonic flow past a helicopte...
The input parameters are presented for a computer program which performs calculations for inviscid i...
The development of a potential-flow/boundary-layer method for calculating subsonic and transonic tur...
The growing application of computational aerodynamics to nonlinear rotorcraft problems is outlined, ...
Aerodynamic research relating to modern helicopters includes the study of three dimensional, unstead...
This report discusses progress made on NASA Cooperative Agreement NCC2-545, 'An Experimental Study o...
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1989.In...
Differential equations and boundary conditions for a rotor blade in forward flight, with subsonic or...
The results are reported of the research on the viscous interactions effects on transonic airfoil de...
The optimum design of the advancing helicopter rotor for high-speed forward flight always involves a...
Two research programs are described which directly relate to the application of natural laminar flow...
Wind tunnel investigation of helicopter directional control in rearward flight in ground effec
A 3-D laminar and turbulent boundary-layer method is developed for compressible flow over swept wing...