Selection of air intake parameters for supersonic-flow operation
Abstract
An optimum system of skewed shock waves is selected for supersonic flight velocities (Mach 4-6) under the condition that the total stream rotation angle behind the skewed shock waves do not exceed a certain critical value corresponding to the onset of sonic flow. The approach proposed here is illustrated by an example in which systems of skewed shock waves are calculated for Mach 6.
- Publication:
-
USSR Rept Eng Equipment JPRS UEQ
- Pub Date:
- March 1985
- Bibcode:
- 1985RpEE........89B
- Keywords:
-
- Air Intakes;
- Engine Inlets;
- Ramjet Engines;
- Shock Wave Control;
- Supersonic Flight;
- Aerodynamics;
- Airspeed;
- Mach Number;
- Skewness;
- Supersonic Combustion Ramjet Engines;
- Fluid Mechanics and Heat Transfer