An experimental and computational investigation of the flow field about a transonic airfoil in supercritical flow with turbulent boundary-layer separation
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- Unclassified, Unlimited, Publicly available.
- A combined experimental and computational research program is described for testing and guiding turbulence modeling within regions of separation induced by shock waves incident in turbulent boundary layers. Specifically, studies are made of the separated flow the rear portion of an 18%-thick circular-arc airfoil at zero angle of attack in high Reynolds number supercritical flow. The measurements include distributions of surface static pressure and local skin friction. The instruments employed include highfrequency response pressure cells and a large array of surface hot-wire skin-friction gages. Computations at the experimental flow conditions are made using time-dependent solutions of ensemble-averaged Navier-Stokes equations, plus additional equations for the turbulence modeling.
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 19760021426., Accession ID: 76N28514., NASA-TM-X-73157., and A-6690.
- No Copyright.
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