Inlet Performance Characteristics of a Generalized 1/5.2-Scale Aircraft Model at Transonic and Supersonic Mach Numbers
Inlet Performance Characteristics of a Generalized 1/5.2-Scale Aircraft Model at Transonic and Supersonic Mach Numbers

Author:

Publisher:

Published: 1976

Total Pages: 0

ISBN-13:

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A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-scale composite inlet model to evaluate configuration factors which affected inlet performance. In addition, flow-field surveys were made at the inlet throat and on the fuselage, forward of the inlet cowl lip. Inlet performance parameters in terms of total-pressure recovery, distortion, and turbulence at the simulated compressor face, as well as compressor face and throat station total-pressure contours and diffuser duct static-pressure distributions are presented for various Mach numbers and angles of attack and sideslip. The basic air induction system consisted of a normal-shock-type inlet with a long splitter plate assembly and was located beneath the wing glove in proximity to the fuselage. The total-pressure recovery for the basic inlet system was slightly better than normal shock recovery for cruise attitudes at supersonic Mach numbers. At Mach numbers approaching 2.0, the basic inlet system was operating close to the buzz limit at design engine airflow. Reductions in total-pressure distortion were achieved by increasing the fuselage-to-inlet standoff distance and by inlet duct boundary-layer blowing. (Author).

Inlet Performance Characteristics of a Generalized 1/5.2-Scale Aircraft Model at Transonic and Supersonic Mach Numbers
Inlet Performance Characteristics of a Generalized 1/5.2-Scale Aircraft Model at Transonic and Supersonic Mach Numbers

Author:

Publisher:

Published: 1976

Total Pages: 0

ISBN-13:

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A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-scale composite inlet model to evaluate configuration factors which affected inlet performance. In addition, flow-field surveys were made at the inlet throat and on the fuselage, forward of the inlet cowl lip. Inlet performance parameters in terms of total-pressure recovery, distortion, and turbulence at the simulated compressor face, as well as compressor face and throat station total-pressure contours and diffuser duct static-pressure distributions are presented for various Mach numbers and angles of attack and sideslip. The basic air induction system consisted of a normal-shock-type inlet with a long splitter plate assembly and was located beneath the wing glove in proximity to the fuselage. The total-pressure recovery for the basic inlet system was slightly better than normal shock recovery for cruise attitudes at supersonic Mach numbers. At Mach numbers approaching 2.0, the basic inlet system was operating close to the buzz limit at design engine airflow. Reductions in total-pressure distortion were achieved by increasing the fuselage-to-inlet standoff distance and by inlet duct boundary-layer blowing. (Author).

Results of a 0.1-scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers
Results of a 0.1-scale B-1 Inlet Model Test at Transonic and Supersonic Mach Numbers

Author: F. J. Graham

Publisher:

Published: 1971

Total Pages: 150

ISBN-13:

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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).

Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers
Results of a 0.2-scale B-1 Inlet Verification Model Test at Transonic and Supersonic Mach Numbers

Author: John F. Riddell

Publisher:

Published: 1972

Total Pages: 250

ISBN-13:

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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).

Inlet Performance Characteristics of a Generalized 1/5.2-scale Aircraft Model at Transonic and Supersonic Mach Numbers
Inlet Performance Characteristics of a Generalized 1/5.2-scale Aircraft Model at Transonic and Supersonic Mach Numbers

Author: Jimmy Walker

Publisher:

Published: 1976

Total Pages: 202

ISBN-13:

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A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-scale composite inlet model to evaluate configuration factors which affected inlet performance. In addition, flow-field surveys were made at the inlet throat and on the fuselage, forward of the inlet cowl lip. Inlet performance parameters in terms of total-pressure recovery, distortion, and turbulence at the simulated compressor face, as well as compressor face and throat station total-pressure contours and diffuser duct static-pressure distributions are presented for various Mach numbers and angles of attack and sideslip. The basic air induction system consisted of a normal-shock-type inlet with a long splitter plate assembly and was located beneath the wing glove in proximity to the fuselage. The total-pressure recovery for the basic inlet system was slightly better than normal shock recovery for cruise attitudes at supersonic Mach numbers. At Mach numbers approaching 2.0, the basic inlet system was operating close to the buzz limit at design engine airflow. Reductions in total-pressure distortion were achieved by increasing the fuselage-to-inlet standoff distance and by inlet duct boundary-layer blowing. (Author).