Author: Earl C. WatsonPublisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 32
Book Description
An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular Internal-compression Inlets Having Translatable Centerbodies and Provisions for Boundary-layer Removal
Author: Earl C. WatsonPublisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 32
Book Description
Scramjet Propulsion
Author: E. T. CurranPublisher: AIAA
ISBN: 9781600864414
Category : Airplanes
Languages : en
Pages : 1354
Book Description
Experimental Investigation of a Mach 5 Isentropic Spike Inlet at and Below Design Speed
Author: Leonard E. StittPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 22
Book Description
An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular-internal-contraction Inlets with Translating Centerbodies
Author: Emmet A. MossmanPublisher:
ISBN:
Category :
Languages : en
Pages : 25
Book Description
Experimental Investigation of the Performance of a Mach-2.7 Two-dimensional Bifurcated Duct Inlet with 30 Percent Internal Contraction
Author: Joseph F. WasserbauerPublisher:
ISBN:
Category :
Languages : en
Pages : 50
Book Description
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compression bifurcated duct inlet system designed for a free-stream Mach number of 2.7. Thirty percent of the supersonic area contraction occurred internally. A movable ramp was used to vary the contraction ratio for off-design operation. Boundary layer bleed regions were located on the cowl, centerbody, and sidewall surfaces. There were also provisions for vortex generators on the cowl and centerbody of the subsonic diffuser. Data were obtained over the Mach number range of 2.0 to 2.8 and at angles of yaw from 0 deg. to the maximum value prior to inlet un-start. The test at Mach 2.8 was to obtain data for an over- speed condition. The Reynolds number varied from 2.5 to 2.3 million/ft for Mach numbers above 2.5. At Mach numbers of 2.5 and lower, the Reynolds number was set at 2.5 million/ft. Bleed patterns, vortex generator patterns, and ramp position were varied, and three inlet configurations were selected for more extensive study. Two of these configurations had self-starting capability. The self-starting configuration that was developed produced 89 percent total pressure recovery at the compressor face station with 6.8 percent total bleed. The compressor face distortion was about 16 percent. Vortex generators were extremely effective in re-distributing flow but were not as effective in reducing distortion. Excellent flow symmetry was achieved between the separated halves of the inlet, and twin-duct instability was not observed. The ramp tip shock was steeper than expected. This caused the cowl lip shock to be reflected from the ramp instead of being cancelled at the shoulder. However, peak recovery at the throat was still obtained with the ramp near the design position.
Experimental Investigation of a Mach 6 Fixed-geometry Inlet Featuring a Swept External-internal Compression Flow Field
Author: Marvin G. TorrencePublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 66
Book Description
Experimental Investigation of the Performance of a Mach-2. 7 Two-Dimensional Bifurcated Duct Inlet with 30 Percent Internal Contraction
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781722219505
Category :
Languages : en
Pages : 46
Book Description
An experimental study was conducted to determine the performance of a two-dimensional, mixed-compression bifurcated duct inlet system designed for a free-stream Mach number of 2.7. Thirty percent of the supersonic area contraction occurred internally. A movable ramp was used to vary the contraction ratio for off-design operation. Boundary layer bleed regions were located on the cowl, centerbody, and sidewall surfaces. There were also provisions for vortex generators on the cowl and centerbody of the subsonic diffuser. Data were obtained over the Mach number range of 2.0 to 2.8 and at angles of yaw from 0 deg. to the maximum value prior to inlet un-start. The test at Mach 2.8 was to obtain data for an over- speed condition. The Reynolds number varied from 2.5 to 2.3 million/ft for Mach numbers above 2.5. At Mach numbers of 2.5 and lower, the Reynolds number was set at 2.5 million/ft. Bleed patterns, vortex generator patterns, and ramp position were varied, and three inlet configurations were selected for more extensive study. Two of these configurations had self-starting capability. The self-starting configuration that was developed produced 89 percent total pressure recovery at the compressor face station with 6.8 percent total bleed. The compressor face distortion was about 16 percent. Vortex generators were extremely effective in re-distributing flow but were not as effective in reducing distortion. Excellent flow symmetry was achieved between the separated halves of the inlet, and twin-duct instability was not observed. The ramp tip shock was steeper than expected. This caused the cowl lip shock to be reflected from the ramp instead of being cancelled at the shoulder. However, peak recovery at the throat was still obtained with the ramp near the design position. Wasserbauer, J. F. and Meleason, E. T. and Burstadt, P. L. Glenn Research Center RTOP 537-02-23...
Experimental Investigation of Generic Three-dimensional Sidewall-compression Scramjet Inlets at Mach 6 in Tetrafluoromethane
Author: Scott D. HollandPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 52
Book Description
An Experimental Investigation at a Mach Number of 4.95 of Flow in the Vicinity of a 90 Degree Interior Corner Alined with the Free-stream Velocity
Author: P. Calvin StainbackPublisher:
ISBN:
Category : Mach number
Languages : en
Pages : 34
Book Description
Investigation of a Mixed Compression Axisymmetric Inlet at Mach Number 5.3
Author: Eldon A. LathamPublisher:
ISBN:
Category : Axial flow
Languages : en
Pages : 44
Book Description
