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F-8 supercritical wing flight pressure, boundary layer, and wake measurements and comparisons with wind tunnel data
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Banner, R. D. Montoya, L. C. |
| Copyright Year | 1977 |
| Description | Data for speeds from Mach 0.50 to Mach 0.99 are presented for configurations with and without fuselage area-rule additions, with and without leading-edge vortex generators, and with and without boundary-layer trips on the wing. The wing pressure coefficients are tabulated. Comparisons between the airplane and model data show that higher second velocity peaks occurred on the airplane wing than on the model wing. The differences were attributed to wind tunnel wall interference effects that caused too much rear camber to be designed into the wing. Optimum flow conditions on the outboard wing section occurred at Mach 0.98 at an angle of attack near 4 deg. The measured differences in section drag with and without boundary-layer trips on the wing suggested that a region of laminar flow existed on the outboard wing without trips. |
| File Size | 7631597 |
| Page Count | 195 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770022154 |
| Archival Resource Key | ark:/13960/t4xh4d524 |
| Language | English |
| Publisher Date | 1977-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Subsonic Wind Tunnels F-8 Aircraft Subsonic Flow Wind Tunnel Tests Aircraft Wakes Flight Load Recorders Supercritical Wings Boundary Layers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
