Aerodynamic Shape Design including Boundary-Layer Transition Analysis

Transition analysis of a Mach 1.5 wing/body configuration: shown are pressure coefficients on the numerical mesh and laminar instability composite N-factors on the wing. An N-factor of 1 or greater (white areas) denotes turbulent flow. The airfoils and fuselage are shaped to minimize total drag including the effect of the aerodynamic shape on transition location.