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Next: Up: Solution of Mach Angle Previous: The case of D Index
The pressure ratio can be expressed as
The density ratio can be expressed as
The temperature ratio expressed as
The Mach number after the shock is
The ratio of the total pressure can be expressed as
Even though the solution for these variables, and , is unique, the possible range deflection angle, , is limited. Examining equation (13.51) shows that the shock angle, , has to be in the range of (see Figure 13.9). The range of given , upstream Mach number , is limited between and .
Next: Up: Solution of Mach Angle Previous: The case of D Index Created by:Genick Bar-Meir, Ph.D.
On: 2007-11-21 include("aboutPottoProject.php"); ?>