An investigation of a lifting 10-percent-thick symmetrical double-wedge airfoil at mach number up to 1

Milton D. Humphreys
naca-tn-3306
Nov 1954


Pressure measurements on the surface of a two-dimensional symmetrical double-wedge airfoil have been obtained from tests in the Langley 4- by 19-inch semiopen tunnel at lifting conditions and at Mach numbers up to 1. The object of this investigation was to obtain normal-force, pressure-drag, and pitching-moment data and to compare them with available experimental and theoretical results.

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http://naca.central.cranfield.ac.uk/reports/1954/naca-tn-3306.pdf