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| Author | : R. C. German |
| Publisher | : |
| Total Pages | : 340 |
| Release | : 1974 |
| Genre | : Jet engines |
| ISBN | : |
| Author | : R. C. German |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1974 |
| Genre | : Jet engines |
| ISBN | : |
| Author | : John F. Riddell |
| Publisher | : |
| Total Pages | : 250 |
| Release | : 1972 |
| Genre | : Airplanes |
| ISBN | : |
Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1972 |
| Genre | : |
| ISBN | : |
Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1972 |
| Genre | : |
| ISBN | : |
Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).
| Author | : F. J. Graham |
| Publisher | : |
| Total Pages | : 150 |
| Release | : 1971 |
| Genre | : Airplanes |
| ISBN | : |
Results are presented of a wind tunnel investigation of a 0.1-scale model of the left-hand dual inlet air induction system of the B-1 aircraft. The test was conducted from Mach number 0.55 to 2.2 over an angle-of-attack range from -4 to 13 deg and yaw angles of -8 to 5 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion, and turbulence index is presented as a function of inlet mass-flow ratios for various inlet geometries and model attitudes. The total-pressure recovery of the mixed-compression inlet was very good, but the total-pressure distortion at critical massflow ratios was higher than normally desired for satisfactory turbine engine operation. Best performance was realized with ramp and throat height schedules determined from previous testing. Effects of angle of attack and yaw were seen as general sidewash effects. The addition of canard-type fins had negligible effect on inlet performance. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1971 |
| Genre | : |
| ISBN | : |
Results are presented of a wind tunnel investigation of a 0.1-scale model of the left-hand dual inlet air induction system of the B-1 aircraft. The test was conducted from Mach number 0.55 to 2.2 over an angle-of-attack range from -4 to 13 deg and yaw angles of -8 to 5 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion, and turbulence index is presented as a function of inlet mass-flow ratios for various inlet geometries and model attitudes. The total-pressure recovery of the mixed-compression inlet was very good, but the total-pressure distortion at critical massflow ratios was higher than normally desired for satisfactory turbine engine operation. Best performance was realized with ramp and throat height schedules determined from previous testing. Effects of angle of attack and yaw were seen as general sidewash effects. The addition of canard-type fins had negligible effect on inlet performance. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1971 |
| Genre | : |
| ISBN | : |
Results are presented of a wind tunnel investigation of a 0.1-scale model of the left-hand dual inlet air induction system of the B-1 aircraft. The test was conducted from Mach number 0.55 to 2.2 over an angle-of-attack range from -4 to 13 deg and yaw angles of -8 to 5 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion, and turbulence index is presented as a function of inlet mass-flow ratios for various inlet geometries and model attitudes. The total-pressure recovery of the mixed-compression inlet was very good, but the total-pressure distortion at critical massflow ratios was higher than normally desired for satisfactory turbine engine operation. Best performance was realized with ramp and throat height schedules determined from previous testing. Effects of angle of attack and yaw were seen as general sidewash effects. The addition of canard-type fins had negligible effect on inlet performance. (Author).
| Author | : H. E. McDill |
| Publisher | : |
| Total Pages | : 416 |
| Release | : 1975 |
| Genre | : Jet engines |
| ISBN | : |
| Author | : H. E. McDill |
| Publisher | : |
| Total Pages | : 330 |
| Release | : 1972 |
| Genre | : Eagle (Jet fighter plane) |
| ISBN | : |
