A procedure for calculating 3-D, compressible laminar boundary layer flow on general fuselage shapes is described. The boundary layer solutions can be obtained in either nonorthogonal 'body oriented' coordinates or orthogonal streamline coordinates. The numerical procedure is 'second order' accurate, efficient and independent of the cross flow velocity direction. Numerical results are presented for several test cases, including a sharp cone, an ellipsoid of revolution, and a general aircraft fuselage at angle of attack. Comparisons are made between numerical results obtained using nonorthogonal curvilinear 'body oriented' coordinates and streamline coordinates. Wie, Yong-Sun Unspecified Center BOUNDARY LAYER FLOW; COMPRESSIBLE BOUNDARY LAYER; COMPUTATIONAL FLUID DYNAMICS; FUSELAGES; LAMINAR BOUNDARY LAYER; THREE DIMENSIONAL BOUNDARY LAYER; ANGLE OF ATTACK; COMPUTER PROGRAMS; CONES; COORDINATES; CROSS FLOW; ELLIPSOIDS...

A procedure for calculating 3-D, compressible laminar boundary layer flow on general fuselage shapes is described. The boundary layer solutions can be obtained in either nonorthogonal 'body oriented' coordinates or orthogonal streamline coordinates. The numerical procedure is 'second order' accurate, efficient and independent of the cross flow velocity direction. Numerical results are presented for several test cases, including a sharp cone, an ellipsoid of revolution, and a general aircraft fuselage at angle of attack. Comparisons are made between numerical results obtained using nonorthogonal curvilinear 'body oriented' coordinates and streamline coordinates. Wie, Yong-Sun Unspecified Center BOUNDARY LAYER FLOW; COMPRESSIBLE BOUNDARY LAYER; COMPUTATIONAL FLUID DYNAMICS; FUSELAGES; LAMINAR BOUNDARY LAYER; THREE DIMENSIONAL BOUNDARY LAYER; ANGLE OF ATTACK; COMPUTER PROGRAMS; CONES; COORDINATES; CROSS FLOW; ELLIPSOIDS...