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A wind-tunnel investigation of the application of the nasa supercritical airfoil to a variable-wing-sweep fighter airplane
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ayers, T. G. |
| Copyright Year | 1973 |
| Description | An investigation was conducted in the Langley 8 foot transonic pressure tunnel and the Langley Unitary Plan wind tunnel to evaluate the effectiveness of three variations of the NASA supercritical airfoil as applied to a model of a variable wing sweep fighter airplane. Wing panels incorporating conventional NACA 64A series airfoil with 0.20 and 0.40 camber were used as bases of reference for this evaluation. Static force and moment measurements were obtained for wing leading edge sweep angles of 26, 33, 39, and 72.5 degrees. Fluctuating wing root bending moment data were obtained at subsonic speeds to determine buffet characteristics. Subsonic data were also obtained for determining the effects of wing transition location and spoiler deflection. Limited lateral directional data are included for the conventional 0.20 cambered wing and the supercritical wing. |
| File Size | 13291299 |
| Page Count | 269 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830002758 |
| Archival Resource Key | ark:/13960/t6450fr33 |
| Language | English |
| Publisher Date | 1973-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aeronautics (general) Variable Sweep Wings Transonic Wind Tunnels Wing Planforms Attack Aircraft Aerodynamics Airfoils Aircraft Models Cambered Wings Wind Tunnel Tests Supercritical Wings Aerodynamic Characteristics Buffeting Fighter Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
