Simulated transonic flows for aircraft with nacelles, pylons, and wingletsA computational method which simulates transonic flow about wing-fuselage configurations has been extended to include the treatment of multiple body and non-planar wing surfaces. The finite difference relaxation scheme is characterized by a modified small disturbance flow equation and multiple embedded grid system. Wing-body combinations with as many as four nacelles/pods, four pylons, and wing-tip-mounted winglets can be analyzed. A scheme for modeling inlet spillage and engine exhaust interference effects has been included. Computed results are correlated with experimental data for three transport configurations.
Document ID
19800039763
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Boppe, C. W. (Grumman Aerospace Corp. Bethpage, NY, United States)
Stern, M. A. (Grumman Aerospace Corp. Bethpage, N.Y., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 80-0130
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Pasadena, CA
Start Date: January 14, 1980
End Date: January 16, 1980
Sponsors: American Institute of Aeronautics and Astronautics