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Wing planform effects at supersonic speeds for an advanced fighter configuration
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Miller, D. S. Wood, R. M. |
| Copyright Year | 1984 |
| Description | Four advanced fighter configurations, which differed in wing planform and airfoil shape, were investigated in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.80, 2.00, and 2.16. Supersonic data were obtained on the four uncambered wings, which were each attached to a single fighter fuselage. The fuselage geometry varied in cross-sectional shape and had two side-mounted, flow-through, half-axisymmetric inlets. Twin vertical tails were attached to the fuselage. The four planforms tested were a 65 deg delta wing, a combination of a 20 deg trapezoidal wing and a 45 deg horizontal tail, a 70 deg/30 deg cranked wing, and a 70 deg/66 deg crank wing, where the angle values refer to the leading-edge sweep angle of the lifting-surface planform. Planform effects on a single fuselage representative of an advanced fighter aircraft were studied. Results show that the highly swept cranked wings exceeded the aerodynamic performance levels, at low lift coefficients, of the 65 deg delta wing and the 20 deg trapezoidal wing at trimmed and untrimmed conditions. |
| File Size | 5808409 |
| Page Count | 118 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19840012418 |
| Archival Resource Key | ark:/13960/t2q57ff2d |
| Language | English |
| Publisher Date | 1984-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Directional Stability Supersonic Airfoils Wing Planforms Wind Tunnel Tests Lateral Stability Angle of Attack Aerodynamic Characteristics Fighter Aircraft Aircraft Configurations Longitudinal Stability Leading Edge Sweep Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
