Near wake and far wake nozzle jet effects on forces on the aft end of a .09 scale simulated fighter airplane were tested at Mach numbers of .6, .85, 1.27, 1.7 and 2.0. Cold air was used for producing the simulated engine exhaust jets. Model configuration changes included various boattail angles, inlet bluntness, wing sweep, and horizontal tail on and off. Data obtained include chord force, normal force, and pitching moment from an internal balance, external static pressure distributions and chord force determined from integrated pressures, and schlieren and shadowgraph photographs of exhaust plumes. (Author)
Propulsion System Integration and Test Program (Steady State). Part III. Nozzle Interaction Drag Tests
1969
506 pages
Report
Keine Angabe
Englisch
Jet & Gas Turbine Engines , Fluid Mechanics , Aircraft , Jet fighters , Turbojet exhaust nozzles , Convergent divergent nozzles , Drag , Interactions , Wake , Airplane models , Scale , Nozzle gas flow , Jet engine inlets , Subsonic characteristics , Pressure , Supersonic characteristics , Pitch(Motion)