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Accession Number N14-0000467
Title Testing of the Trim Tab Parametric Model in NASA Langley's Unitary Plan Wind Tunnel.
Publication Date Jun 2013
Media Count 16p
Personal Author A. M. Korzun A. N. Watkins K. J. Murphy K. T. Edquist
Abstract In support of NASA's Entry, Descent, and Landing technology development efforts, testing of Langley's Trim Tab Parametric Models was conducted in Test Section 2 of NASA Langley's Unitary Plan Wind Tunnel. The objectives of these tests were to generate quantitative aerodynamic data and qualitative surface pressure data for experimental and computational validation and aerodynamic database development. Six component force-and-moment data were measured on 38 unique, blunt body trim tab configurations at Mach numbers of 2.5, 3.5, and 4.5, angles of attack from -4deg to +20deg, and angles of sideslip from 0deg to +8deg. Configuration parameters investigated in this study were forebody shape, tab area, tab cant angle, and tab aspect ratio. Pressure Sensitive Paint was used to provide qualitative surface pressure mapping for a subset of these flow and configuration variables. Over the range of parameters tested, the effects of varying tab area and tab cant angle were found to be much more significant than varying tab aspect ratio relative to key aerodynamic performance requirements. Qualitative surface pressure data supported the integrated aerodynamic data and provided information to aid in future analyses of localized phenomena for trim tab configurations.
Keywords Aerodynamic characteristics
Angle of attack
Aspect ratio
Computational fluid dynamics
Data bases
Pressure sensitive paints
Supersonic speed
Tabs(Control surfaces)

Source Agency National Aeronautics and Space Administration
NTIS Subject Category 51A - Aerodynamics
81C - Fuel & Propellant Tanks
84C - Manned Spacecraft
Corporate Author National Aeronautics and Space Administration, Hampton, VA. Langley Research Center.
Document Type Conference proceedings
Title Note N/A
NTIS Issue Number 1416
Contract Number N/A

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