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Preliminary flight-determined subsonic lift and drag characteristics of the x-29a forward-swept-wing airplane
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Huckabine Sr., Thomas Hicks, John W. |
| Copyright Year | 1989 |
| Description | The X-29A subsonic lift and drag characteristics determined, met, or exceeded predictions, particularly with respect to the drag polar shapes. Induced drag levels were as great as 20 percent less than wind tunnel estimates, particularly at coefficients of lift above 0.8. Drag polar shape comparisons with other modern fighter aircraft showed the X-29A to have a better overall aircraft aerodynamic Oswald efficiency factor for the same aspect ratio. Two significant problems arose in the data reduction and analysis process. These included uncertainties in angle of attack upwash calibration and effects of maneuver dynamics on drag levels. The latter problem resulted from significantly improper control surface automatic camber control scheduling. Supersonic drag polar results were not obtained during this phase because of a lack of engine instrumentation to measure afterburner fuel flow. |
| File Size | 1803646 |
| Page Count | 48 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910019863 |
| Archival Resource Key | ark:/13960/t9z081m1z |
| Language | English |
| Publisher Date | 1989-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Flight Tests Aerodynamic Drag Lift Drag Ratio Swept Forward Wings Aerodynamic Coefficients Induced Drag Aspect Ratio Lift X-29 Aircraft Aerodynamic Configurations Subsonic Flow Upwash Control Surfaces Camber Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
