Subsonic Investigation of a Leading-Edge Boundary Layer Control Suction System on a High-Speed Civil Transport Configuration
Subsonic Investigation of a Leading-Edge Boundary Layer Control Suction System on a High-Speed Civil Transport Configuration
- Neue Suche nach: Campbell, Bryan A.
- Neue Suche nach: Applin, Zachary T.
- Neue Suche nach: Kemmerly, Guy T.
- Neue Suche nach: Coe, Paul L., Jr.
- Neue Suche nach: Owens, D. Bruce
- Neue Suche nach: Gile, Brenda E.
- Neue Suche nach: Parikh, Pradip G.
- Neue Suche nach: Smith, Don
- Neue Suche nach: Campbell, Bryan A.
- Neue Suche nach: Applin, Zachary T.
- Neue Suche nach: Kemmerly, Guy T.
- Neue Suche nach: Coe, Paul L., Jr.
- Neue Suche nach: Owens, D. Bruce
- Neue Suche nach: Gile, Brenda E.
- Neue Suche nach: Parikh, Pradip G.
- Neue Suche nach: Smith, Don
A wind tunnel investigation of a leading edge boundary layer control system was conducted on a High Speed Civil Transport (HSCT) configuration in the Langley 14- by 22-Foot Subsonic Tunnel. Data were obtained over a Mach number range of 0.08 to 0.27, with corresponding chord Reynolds numbers of 1.79 x 10(exp 6) to 5.76 x 10(exp 6). Variations in the amount of suction, as well as the size and location of the suction area, were tested with outboard leading edge flaps deflected 0 and 30 deg and trailing-edge flaps deflected 0 and 20 deg. The longitudinal and lateral aerodynamic data are presented without analysis. A complete tabulated data listing is also presented herein.
Dokumentinformationen
Subsonic Investigation of a Leading-Edge Boundary Layer Control Suction System on a High-Speed Civil Transport Configuration
1999-12-01
Report
Keine Angabe
Englisch