NONDIMENSIONAL CALCULATION OF TURBULENT BOUNDARY-LAYER DEVELOPMENT IN TWO-DIMENSIONAL NOZZLES OF SUPERSONIC WIND TUNNELS
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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The method developed by Maurice Tucker Approximate Calculation of Turbulent Boundary Layer Development in Compressible Flow, NACA TN 2337, 1951 for calculating the growth of turbulent boundary layers in two-dimensional compressible flow has been adapted to the computation of a dimensionless boundary-layer parameter. Equations and calculational procedures are presented for correcting two-dimensional supersonic nozzles for boundary-layer growth using only one or two tables, depending on the geometry. The tables are supplied for the Mach number range fro 1.5 to 8.0. Agreement of calculated data with measured data and effect of Mach number distribution are shown.
- Fluid Mechanics