LIFTING/PROPULSIVE EJECTOR

AN ANALYSIS OF THE FLOW OF A COMPRESSIBLE FLUID THROUGH A STATIONARY OR TRANSLATING EJECTOR HAS DESCRIBED TWO DISTINCTSOLUTIONS TO THE EQUATIONS GOVERNING THE COMPLETELY MIXED PRIMARY AND SECONDARY FLOWS. BOTH SOLUTIONS PROVIDE THE ESSENTIAL DATA REQUIRED FOR THE DESIGN OF THE EJECTOR GEOMETRY, THE PRIMARY AND SECONDARY MASS FLOWS, THE FLOW PROPERTIES WITHIN THE EJECTOR, AND THE THRUST AUGMENTATION FOR EVERY REASONABLE FLIGHT AND INJECTED GAS CONDITION. HOWEVER, THE SECOND SOLUTION, THAT RESULTS IN A SUPERSONIC MIXED FLOW, PROVIDES A CONSIDERABLY LARGER THRUST AUGMENTATION OVER THE ENTIRE RANGE OF FLIGHT CONDITIONS THANDOES THE FIRST SOLUTION, WHICH RESULTS IN A SUBSONIC MIXED FLOW. THIS STUDY IS INTENDED TO PROVIDE A MEANS FOR SELECTION OF A SUITABLE WIND TUNNEL AND FOR THE DESIGN OF A MODEL AND FORMULATION OF A TEST PLAN TO CORRELATE THE REALISTICALLY ACHIEVABLE PERFORMANCE OF THESE TYPES OF EJECTORS WITH THE THEORY.