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An experimental investigation of dynamic ground effect
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lee, Pai Hung Muirhead, Vincent U. Lan, C. Edward |
| Copyright Year | 1987 |
| Description | A 60-degree delta wing, an F-106B, and an XB-70 model with and without flap deflections were tested in static and dynamic ground effect in the 36-by 51-inch subsonic wind tunnel at the University of Kansas. Dynamic ground effect was measured with movable sting support. For flow visualization, a tufted wire grid was mounted on the movable sting behind the model. Test results showed that lift and drag increments in dynamic ground effect were always lower than static values. Effect of the trailing edge flap deflections on lift increments was slight. The fuselage reduced the lift increments at a given ground height. From flow visualization under static conditions, the vortex core was seen to enlarge as the ground was approached. |
| File Size | 1801907 |
| Page Count | 84 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880003076 |
| Archival Resource Key | ark:/13960/t81k4987c |
| Language | English |
| Publisher Date | 1987-12-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Dynamic Response Deflection F-106 Aircraft Static Tests Lift Drag Vortices Delta Wings Flaps Control Surfaces Wind Tunnel Tests Flow Visualization B-70 Aircraft Ground Effect Aerodynamics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
