University of North Texas Digital Library (University of North Texas) · 1956 · 14 citations · 0 references
Open access
EngineeringAerospace EngineeringAerodynamicsSurface EngineeringSurface ScienceBoundary Layer FlowBoundary LayersBoundary-layer DynamicsBoundary-layer TheorySupersonic AerodynamicsThermal Boundary LayersBoundary-layer TransitionMach NumberMach Number EffectsSupersonic Boundary LayersSurface CoolingSurface Cooling EffectsSurface TemperatureViscous Boundary Layer
Recent results of the effects of Mach number, stream turbulence, leading-edge geometry, leading-edge sweep, surface temperature, surface finish, pressure gradient, and angle of attack on boundary-layer transition are summarized. Factors that delay transition are nose blunting, surface cooling, and favorable pressure gradient. Leading-edge sweep and excessive surface roughness tend to promote early transition. The effects of leading-edge blunting on two-dimensional surfaces and surface cooling can be predicted adequately by existing theories, at least in the moderate Mach number range.