Description of Q_sonic Experimental Data Figure

This figure, taken from Mayer and Paynter (1994), depicts experimental sonic mass flow coefficient data (Q_sonic) as a function of the ratio of plenum static pressure (p_plenum) to local boundary layer total pressure (p_{t plenum}). The first set of data, obtained by McLafferty and Ranard (1958), is for a bleed hole angle of 20° relative to the local flow velocity. The second set of data, obtained by Syberg and Hickox (1972), is for a bleed hole angle of 90°. Both sets of data show a decrease in Q_sonic as the pressure ratio increases. The values for Q_sonic are generally larger, indicating fewer losses, for flows with a lower local boundary layer edge Mach number.

References:

• Mayer, D. W., and Paynter, G. C. (1994) "Boundary Conditions for Unsteady Supersonic Inlet Analyses," AIAA Journal, Vol. 32, No. 6, pp. 1200-1206].
  
  
• McLafferty, G., and Ranard, E. (1958) "Pressure Losses and Flow Coefficients of Slanted Perforations Discharging from Within a Simulated Supersonic Inlet," United Aircraft Corporation, Report R-0920-1, Dec. 1958.
  
  
• Syberg, J., and Hickox, T. E. (1972) "Design of a Bleed System for a Mach 3.5 Inlet," NASA CR-2187, Sept. 1972.