Lift-curve slopes determined in flight on a flexible swept-wing jet bomber /
William S. Aiken, Jr., and Raymond A. Fisher.

Description

Main Author

Aiken, William S., Jr.

Related Names

Fisher, Raymond A.
Langley Aeronautical Laboratory.
United States. National Advisory Committee for Aeronautics.

Language(s)

English

Published

Washington, D.C. : National Advisory Committee for Aeronautics, [1956]

Subjects

Charts, diagrams, etc.
Airplanes > Airplanes / Flight testing.
Angle of attack (Aerodynamics)
Acceleration (Mechanics) > Acceleration (Mechanics) / Measurement.
Aerodynamic load.
Lift (Aerodynamics)
Airplanes > Airplanes / Wings, Swept-back.
Airplanes, Military > Airplanes, Military / Bombers.

Summary

An analysis is made of the effects of Mach number and dynamic pressure on the lift-curve slope of a large flexible swept-wing jet-propelled airplane by using flight measurements of normal acceleration and angle of attack with auxiliary instrumentation as needed. The methods and procedures used to correct the flight measurements (obtained in abrupt push-pull maneuvers) and to convert the flight test data to equivalent rigid conditions for comparison with rigid-model wind-tunnel tests are described in detail. The airplane angle of zero lift and the airplane-less-tail angle of zero lift for the Mach number range of the flight tests (0.42 to 0.81) are also presented. Excellent agreement was obtained in the comparison between flight and wind-tunnel rigid lift-curve slopes and angles of zero lift.

Note

NACA Research Memorandum L56E21a.
On front cover: "Classification Changed to Unclassified, Authority: NACA Research Abstract No. 120. Effective Date; September 13, 1957 WHL."
"December 19, 1956."
Cover title.

Physical Description

49 pages : illustrations ; 27 cm.

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