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The effect of boundary-layer control by suction and several high-lift devices on the longitudinal aerodynamic characteristics of a 47.5 degree sweptback wing-fuselage combination
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1948 |
| Description | An investigation has been made in the Langley full-scale tunnel of a 47.5 degree sweptback wing-fuselage combination equipped for boundary-layer control by suction. The wing aspect ratio was 3.5, the taper ratio was 0.5, and the airfoil sections normal to the quarter-chord line were NACA 64(sub 1)-A112. The wing configurations tested included the wing with various combinations of extensible leading-edge and split flaps. The effect of Reynolds number, suction-slot location and suction flow coefficient on the aerodynamic characteristics was determined for the model at zero yaw over a range of angle of attack. |
| File Size | 21620664 |
| Page Count | 45 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930085410 |
| Archival Resource Key | ark:/13960/t06x3pm7t |
| Language | English |
| Publisher Date | 1948-11-04 |
| Access Restriction | Open |
| Subject Keyword | Wing-fuselage Combinations - Airplanes Boundary Layer - Complete Wings Stability, Longitudinal - Static High-lift Devices - Complete Wings Reynolds Number Effects - Complete Wings 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 |
