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PAN AIR Application to the F-106BThe PAN AIR computer code was employed in the present study to investigate the aerodynamic effects of the various geometrical changes and flow conditions on a configuration similar to the F-106B half-airplane tested in the Langley 30x60-foot wind tunnel. The various geometries studied included two forebodies (original and shortened), two inlet flow conditions (open and closed) two vortex flap situations (off and on). The attached flow theoretical solutions were obtained for Mach number of 0.08 and angle of attack of 8 deg., 10 deg., 12 deg., and 14 deg. In general this investigation revealed that the shortening of the forebody or closing of the inlet produced only a small change in the overall aerodynamic coefficients of the basic F-106B configuration throughout the examined angles of attack. However, closing the inlet of the configuration resulted in a slightly higher drag level at low angles of attack. Furthermore, at and above 10 deg. angle of attack, it was shown that the presence of the vortex flap causes an increase in the total lift and drag. Also, these theoretical results showed the expected reduction in longitudinal stability level with addition of the vortex flap to the basic F-106B configuration.
Document ID
19860021226
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Farhad Ghaffari (ViGYAN (United States) Hampton, Virginia, United States)
Date Acquired
September 5, 2013
Publication Date
August 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:178165
NASA-CR-178165
Accession Number
86N30698
Funding Number(s)
PROJECT: RTOP-505-60-21-02
CONTRACT_GRANT: NAS1-17919
Distribution Limits
Public
Copyright
Public Use Permitted.

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