Calculated results for oscillating T-tails in subsonic flow and comparison with experiments
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(1967)
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©1967 National Aerospace Laboratory NLR
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Publication Year
1967
Copyright
©1967 National Aerospace Laboratory NLR
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Abstract
A calculation programme to determine pressure distributions on oscillating T-tails in subsonic flow is briefly described. Calculated results are given and compared with measured results for a number of T-tail configurations. The influence of reflection by wind tunnel walls and fuselage is discussed