Accession Number:

AD0262312

Title:

STATIC LATERAL CHARACTERISTICS AT HIGH SUBSONIC SPEEDS OF A COMPLETE AIRPLANE MODEL WITH A HIGHLY TAPERED WING HAVING THE 0.80 CHORD LINE UNSWEPT AND WITH SEVERAL TAIL CONFIGURATIONS

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-08-01

Pagination or Media Count:

1.0

Abstract:

An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The aspectratio-3.50 wing had a taper ratio of 0.067 and an unswept 0.80 chord line. The complete model was tested with a wing-chord-plane tail, a Ttail, and a biplane tail combined T-tail and wing-chord-plane tail. The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 over a range of angle of attack of about or - 20 degrees and a range of sideslip of -15 degrees to 13 degrees. Some data were obtained with the horizontal stabilizer deflected. A few tests were also made with the wing tips clipped to an aspect ratio of 3.00. The data show that shock-interference effects between the tail surfaces T-tail can have considerable influence on the directional stability and effective dihedral. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE