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Unsteady Navier-Stokes simulation of the canard-wing-body ramp motionA time-accurate thin-layer Navier-Stokes simulation of the unsteady flowfield is performed for a typical canard-wing-body configuration undergoing ramp motions. The computations are made at a transonic Mach number of 0.90 and for ramp angles from 0 to 15 degrees. Accuracy is determined by comparisons with steady-state experimental data and with spatial and time-step refinement studies. During the ramp motion, the computational results show improved dynamic lift performance and a strong canard-wing interaction for the canard-on configuration. Formation of the canard leading-edge vortex is inhibited in the early stages of the ramp motion. An analysis performed on the transient flowfield after the ramp motion ends shows that the canard vortex rapidly gains strength and vortex breakdown eventually occurs. These characteristics of the canard vortex have significant influences on wing performance.
Document ID
19930064238
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tu, Eugene L.
(NASA Ames Research Center Moffett Field, CA, United States)
Obayashi, Shigeru
(NASA Ames Research Center Moffett Field, CA, United States)
Guruswamy, Guru P.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-3058
Meeting Information
Meeting: AIAA, Fluid Dynamics Conference
Location: Orlando, FL
Country: United States
Start Date: July 6, 1993
End Date: July 9, 1993
Sponsors: AIAA
Accession Number
93A48235
Distribution Limits
Public
Copyright
Other

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