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Wind tunnel force tests in wing systems through large angles of attack
Force tests on a systematic series of wing systems over a range of angle of attack from minus forty-five degrees to plus ninety degrees are covered in this report. The investigation was made on monoplane and biplane wing models to determine the effects of variations of tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweepback, and airfoil profile.
Date:
August 1928
Creator:
Wenzinger, Carl J. & Harris, Thomas A.
System:
The UNT Digital Library
The Effect of Tip Shields on a Horizontal Tail Surface
A series of experiments made in the wind tunnel of the Daniel Guggenheim School of Aeronautics, New York University, on the effect of tip shields on a horizontal tail surface are described and discussed. It was found that some aerodynamic gain can be obtained by the use of tip shields though it is considered doubtful whether their use would be practical.
Date:
August 1928
Creator:
Dronin, Paul V.; Ramsden, Earl I. & Higgins, George J.
System:
The UNT Digital Library