Three-dimensional boundary-layer transition on a swept wing at Mach 3.5

@inproceedings{Cattafesta1995ThreedimensionalBT,
  title={Three-dimensional boundary-layer transition on a swept wing at Mach 3.5},
  author={Louis N. Cattafesta and Venkit Iyer and Jamal A. Masad and Rollin A. King and J. Ray Dagenhart},
  year={1995}
}
Transition on a swept-wing leading-edge model at Mach 3.5 is investigated. Surface pressure and temperature measurements are obtained in the NASA Langley Research Center Supersonic Low-Disturbance Tunnel. For one case, temperature-sensitive paint and a sublimating chemical are used to visualize surface flow features such as transition location. The experimental data are compared with 1) mean-flow results computed as solutions to the thin-layer Navier-Stokes equations and 2) N-factors obtained… CONTINUE READING

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