Accession Number:

ADA801316

Title:

Effect of Finite Span on the Airload Distributions for Oscillating Wings. 1 - Aerodynamic Theory of Oscillating Wings of Finite Span

Personal Author(s):

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE

Report Date:

1947-03-01

Abstract:

A formula is derived based on the assumption of the ratio of span to aspect ratio. Three-dimensionality of flow is incorporate into the two-dimensional theory by adding a correction factor, which was found to be the same for lift, moment and hinge moments, but is dependent on the nature of the flow being dealt with. The range of validity equals that of the lifting-line theory for non-oscillating wings.

Descriptive Note:

Technical note

Pages:

0047

Identifiers:

Communities Of Interest:

Distribution Statement:

Approved for public release; distribution is unlimited.

File Size:

10.72MB