NASA NTRS · 19920074212
Boundary layer study on nozzle wall at hypersonic velocities
Abstract
The boundary layer on the wall of the Hypervelocity Tunnel 9 was investigated with pitot pressure and total temperature measurements. Experimental results are presented for standard and supercooled Mach 14 runs. The boundary layer data at supercooled conditions are compared to numerical predictions made with a Navier-Stokes algorithm including vibrational nonequilibrium and intermolecular force effects. For standard tunnel conditions, the numerical solutions agree well with experimental data. For the supercooled cases, the numerical code predicts the total temperature but overpredicts the pitot pressure.
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Jones, Kenneth M., Dejarnette, Fred R., Griffith, Wayland C., Yanta, William J.. 1992-07-01. Boundary layer study on nozzle wall at hypersonic velocities. https://ntrs.nasa.gov/citations/19920074212
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