Integration effects of pylon geometry and rearward mounted nacelles for a high-wing transportResults of a wind-tunnel study of the effect of pylon cross-sectional shape and tow angle on airplane drag and an aft-mounted nacelle are presented. The 1/24-scale wide-body high-wing transport model was tested in the Langley 16-Foot Transonic Tunnel at free-stream Mach 0.7-0.8 and angles of attack from -3 to 4 degrees. A compression-type pylon is found to have the lowest drag at both Mach 0.7 and 0.8 and to be capable of suppressing the velocities in the inboard region of the pylon-wing junction, reducing the extent of supersonic flow and the probability of flow separation. It is also shown that the D-shaped aft-mounted nacelle has a low interference drag, as do previously tested circular nacelles in the same position.
Document ID
19870058026
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Carlson, John R. (NASA Langley Research Center Hampton, VA, United States)
Lamb, Milton (NASA Langley Research Center Hampton, VA, United States)