Publikationsdatum:
2019-06-27
Beschreibung:
Two methods for determining the virtual origin of turbulent boundary layers in hypersonic flow are evaluated. The results of the analyses are restricted to wind-tunnel models having sharp-edged surfaces with zero or small pressure gradients. Virtual origin and skin friction estimates from these two methods are compared with values from a base method for which the virtual origin is calculated from the measured momentum thickness at a station downstream of boundary layer transition.
Schlagwort(e):
AERODYNAMICS
Materialart:
ASME PAPER 74-APM-V
Format:
text
