A wind tunnel test program was evolved for obtaining experimental performance data on a mach 2.5, two-dimensional, external compression inlet typical of the IPS Tactical Fighter inlet. Tests were conducted at mach numbers of 0.6, 0.85, 0.95, 1.2, 1.3, 1.7 and 2.2. The investigation was intended to provide the data necessary to evaluate installation effects and to substantiate analytic methods of performance predictions. (Author)
Propulsion System Integration and Test Program (Steady State). Part IV. Inlet Drag Tests
1969
248 pages
Report
Keine Angabe
Englisch