Oorebeek et al., 2014 - Google Patents
Bleed and vortex generator effectiveness for separation prevention in a transonic diffuserOorebeek et al., 2014
- Document ID
- 3772273705163440038
- Author
- Oorebeek J
- Babinsky H
- Publication year
- Publication venue
- 7th AIAA flow control conference
External Links
Snippet
Boundary layer flow separation within supersonic inlets remains one of the limiting factors in supersonic aircraft performance. Separations can cause many problems, including reduced thrust and unsteady effects which can damage the inlet structure. 1 Mixed compression …
- 238000000926 separation method 0 title abstract description 88
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
- Y02T50/16—Drag reduction by influencing airflow
- Y02T50/166—Drag reduction by influencing airflow by influencing the boundary layer
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Szwaba | Influence of air-jet vortex generator diameter on separation region | |
| Bruce et al. | Corner effect and asymmetry in transonic channel flows | |
| Flaszynski et al. | Shock wave boundary layer interaction on suction side of compressor profile in single passage test section | |
| Sun | Micro vortex generators for boundary layer control: principles and applications | |
| Verhaagen | Leading-edge radius effects on aerodynamic characteristics of 50-degree delta wings | |
| Wang et al. | Wake-induced transition in the low-Reynolds-number flow over a multi-element airfoil | |
| Vinton et al. | Combined effects of freestream pressure gradient and density ratio on the film cooling effectiveness of round and shaped holes on a flat plate | |
| Tasci et al. | Vortical flow characteristics of a slender delta wing in ground effect | |
| Oorebeek et al. | Experimental and computational investigations of a normal-hole-bled supersonic boundary layer | |
| Oorebeek et al. | Bleed and vortex generator effectiveness for separation prevention in a transonic diffuser | |
| Titchener et al. | The effects of various vortex generator configurations on a normal shock wave/boundary layer interaction | |
| DeMauro et al. | Measurements of 3-D stall cells on 2-D airfoil | |
| Vyas et al. | Experimental Investigation of Normal Shock Boundary-Layer Interaction with Hybrid Flow Control | |
| Disotell et al. | Time-resolved measurements of cellular separation on a stalling airfoil | |
| Watanabe et al. | Stereoscopic PIV measurements of leading edge separation vortices on a cranked arrow wing | |
| Davidson et al. | Influence of transition on the flow downstream of normal shock wave--boundary layer interactions | |
| Alam et al. | Reduction of spanwise flow over a swept wing using an air curtain produced by rectangular slot | |
| Burrows et al. | Control of a transonic shock in a serpentine diffuser using surface fluidic actuation | |
| McNally et al. | Active flow control on an ahmed body-an experimental study | |
| Oorebeek et al. | Comparison of Experimental and Computational Flow Structure Investigations of a Normal-Hole Bled Supersonic Boundary Layer | |
| Jun et al. | Evolution of turbulent boundary layer over a three-dimensional bump | |
| Saha et al. | Modeling and simulation on double delta wing | |
| Dussauge et al. | Wp-1 reference cases of laminar and turbulent interactions | |
| Sathianarayanan et al. | Experimental investigation of a Mach 4 shock-wave turbulent boundary layer interaction near an expansion corner | |
| Vasile et al. | Interaction of a finite-span synthetic-jet and a cross-flow over a sweptback finite wing |