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Determining the lift and drag distributions on a three-dimensional airfoil from flow-field velocity surveys
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Orloff, K. L. |
| Copyright Year | 1977 |
| Description | The application of the incompressible momentum integral equation to a three-dimensional airfoil was reviewed to interpret the resulting equations in a way that suggests a reasonable experimental technique for determining the spanwise distributions of lift and drag. Consideration was given to constraints that must be placed on the character of the vortex wake structure shed by the wing, to provide the familiar relationship between lift and bound vorticity. It is shown that the induced drag distribution is not directly measurable, but can be obtained, via the lift distribution, approximately for a deflected wake and exactly for a planar wake. Moreover, it is shown that it is only necessary to survey a short distance above and below the wing trailing edge. Examples are presented for several typical loading distributions and the results of a numerical simulation of the suggested experiment are discussed. |
| File Size | 16371471 |
| Page Count | 77 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770025135 |
| Archival Resource Key | ark:/13960/t7wm62z2m |
| Language | English |
| Publisher Date | 1977-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Aerodynamic Drag Vortices Flow Distribution Trailing Edges Wind Tunnel Tests Flow Velocity Airfoils Induced Drag Lift Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
