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Intergration effects of d-shaped, underwing, aft-mounted, separate-flow, flow-through nacelles on a high-wing transport
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Lamb, Milton Pendergraft Jr., Odis C. Carlson, John R. |
| Copyright Year | 1987 |
| Description | An experimental investigation was conducted in the Langley 16-Foot Transonic Tunnel at freestream Mach numbers from 0.70 to 0.82 and angles of attack from -3.0 to 4.0 deg to determine the integration effects of D-shaped, underwing, aft-mounted, separate-flow, flow-through nacelles on a high-wing transonic transport configuration. The results showed that the aft-mounted nacelle/pylon produced an increase in lift over that of the wing-body configuration by pressurizing much of the wing lower surface in front of the pylon. For the D-shaped nacelle, a substantial region of supersonic flow over the wing, aft of the lip of the nacelle, cancelled the reduction in drag caused by the increase in pressures ahead of the lip, to increase interference and form drag compared with a similar circular-shaped nacelle. The installed drag of the D=shaped nacelle was essentially the same as that of an aft-mounted circular nacelle from a previous investigation. |
| File Size | 2045725 |
| Page Count | 23 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880001391 |
| Archival Resource Key | ark:/13960/t75t8hx97 |
| Language | English |
| Publisher Date | 1987-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Supersonic Flow Transport Aircraft Transonic Wind Tunnels Wind Tunnel Tests Nacelles Shapes Angle of Attack Separated Flow Aircraft Configurations Interference Drag Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
