Accession Number:

ADA801512

Title:

Effect of Elevator-Profile Modifications and Trailing-Edge Strips on Elevator Hinge-Moment and Other Aerodynamic Characteristics of a Full-Scale Horizontal Tail Surface

Corporate Author:

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS LANGLEY FIELD VA LANGLEY AERONAUTICAL LABORATORY

Report Date:

1945-06-01

Abstract:

From investigations conducted in a high-speed wind tunnel on a horizontal tail surface of a full-scale fighter model, the following results were obtained. A reduction of 6 deg in the trailing-edge angle resulted in incremental changes in the slopes of curves of hinge moment against angle of attack and against elevator angle of approximately -0.0026 and -0.0013. No appreciable loss in effectiveness of trailing-edge strip was observed up to Mach number 0.65.

Descriptive Note:

Wartime rept.

Pages:

0038

Identifiers:

Communities Of Interest:

Distribution Statement:

Approved for public release; distribution is unlimited.

File Size:

1.33MB