Test of NACA 66,2-116, a =
0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane /
William J. Underwood and Frank T. Abbott, Jr.

Description

Main Author

Underwood, William J.

Related Names

Abbott, Frank T.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, [1942]

Subjects

Charts, diagrams, etc.
Wind tunnel testing.
Drag (Aerodynamics)
Lift (Aerodynamics)
Hinge moments (Aerodynamics)
Aerodynamic load.
Flaps (Aerodynamics)
Aerofoils > Aerofoils / Testing.

Summary

Tests were made at the Langley two-dimensional low-turbulence pressure tunnel of a mode of the NACA 66,2-116, a = 0.6 airfoil section representing the root section of the wing for the XP-63 airplane.

Note

Prepared at the Langley Memorial Aeronautical Laboratory, Langley Field, Virginia.
Originally issued as NACA as a Memorandum Report (May 1942).
NACA Wartime Report L-701.

Physical Description

6, [13] pages : illustrations ; 27 cm.

Locate a Print Version

Find in a library

Viewability