Radius of curvature normal to the streamlines.

3DBGB camber line for ARL supersonic cascade.

Normalized parameters comparison.

Mach number distribution plot using fine grid MISES run.

Blade angles for a compressor blade. ξ, β * in , β * out and χ in are

Constraints for the Spline thickness distribution calculation.

Second derivative over turbine blade surface.

Turbine blade hub section in (m , θ) plane. 10 Copyright © 2014 by ASME

Transition location (xt/c) vs angle of attack for the S809 airfoil.

Second derivative over turbine blade surface.

Transition onset momentum thickness Reynolds number (Re θ t ) predicted

Comparison of FSM-FRS (left) and five-hole probe (right) static