Radius of curvature normal to the streamlines.

3rd rotor hub section from EEE NASA report.

Second derivative B-spline with control points.

Second derivative over turbine blade surface.

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

Second derivative over turbine blade surface.

The S-shape section camber line.

Design parameters of the two tested configurations.

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

Second derivative over turbine blade surface.