Accession Number:

ADB805716

Title:

Experimental Determination of Dampling in Roll and Aileron Rolling Effectiveness of Three Wings Having 2, 42, and 62 deg Sweepback

Descriptive Note:

Technical note

Corporate Author:

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY

Personal Author(s):

• Bennett, Charles V.
• Johnson, Joseph L.

Report Date:

1947-05-01

Pagination or Media Count:

21.0

Abstract:

An investigation on damping values in roll is presented. It is seen that these values decreased with increased sweepback. Method of obtaining approximate estimate of this reduction is shown. Damping in roll for all three wings decreased with increasing lift coefficient. Increasing amount of sweepback reduced the tendency toward instability in rolling as the maximum lift was approached and increased the aileron deflection required to produce a given value of the helix angle generated by the wing tip.

Descriptors:

• *ROLL
• *AERODYNAMIC CHARACTERISTICS
• *ALL WING AIRCRAFT
• *AIRFOILS
• WING TIPS
• WINGS
• AILERONS
• DEFLECTION
• DAMPING

Subject Categories:

• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE