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Wind-tunnel investigation of an NACA 23012 airfoil with an 18.05 percent chord Maxwell slat and with trailing-edge flaps
Report presenting an investigation in the 7- by 10-foot wind tunnel of an NACA 23012 airfoil with an 18.05-percent-chord Maxwell leading-edge slat and with a slotted and a split flap. The main purpose of the investigation was to determine the optimum slot gap of the Maxwell slat for, and the aerodynamic section characteristics of, the airfoil with several deflections of both types of flap.
Date:
October 1941
Creator:
McKee, John W.
System:
The UNT Digital Library
Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps
"Additional tests as recommended in reference 1 were made in the 7- by 10-foot wind tunnel of the 1/8-scale model of the Brewster F2A airplane to determine the angle of attack of horizontal tail and the elevator angles required for trim with flaps down" (p. 1).
Date:
October 1941
Creator:
Lowry, John G.
System:
The UNT Digital Library