The purpose of this contribution is to report on the aerothermal performance measurements and calculations carried out around a high-pressure gas turbine rotor blade profile mounted in a two-dimensional linear cascade arrangement. The measurements were performed in the CT-2 facility of the von Karman Institute, allowing a correct simulation of the operating conditions encountered in modern aero-engines. Independent variations of exit Mach (0.8−1.3) and Reynolds numbers (5×105–2×106), free-stream turbulence (1–6 percent) and incidence angle (−14–+11 deg) provided the definition of a detailed data base of test results. The measured quantities were the blade velocity and convective heat transfer coefficient distributions. The first objective of the paper is to open and analyze this data base, which is one of those used at SNECMA for validation purposes. The paper shows the degree of maturity and reliability SNECMA-ONERA Navier–Stokes solvers have now reached for daily use in turbine airfoil design and analysis.

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