Radius of curvature normal to the streamlines.

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

The static pressure rise characteristics of the test facility.

Second derivative B-spline with control points.

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

Design parameters of the two tested configurations.

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

FRF associated for the tuned structure for engine order (EO=3) as

Turbine passage Mach number contours.

Total temperature ratio for Rotor35.

PDF) A Smooth Curvature-Defined Meanline Section Option for a General Turbomachinery Geometry Generator

Turbulent kinetic energy around the blade for the MUR235 test case

Second derivative B-spline with control points.