Investigation by the Transonic-Bump Method of a 35 deg Sweptback Semispan Model Equipped With a Flap Operated by a Series of Servovanes Located Ahead of and Geared to the Flap
Abstract
An investigation was made in the Langley high-speed 7- by 10-foot tunnel to determine the feasibility of using a servovane control at high-subsonic and low-transonic speeds. This servovane control could presumedly be deflected with relatively low control forces compared to flap-type controls. The control was tested on an untapered semi span wing of aspect ratio 3.04 with 35 deg of sweepback and a modified NACA 66-009 airfoil section perpendicular to the leading edge. Throughout the speed range tested (Mach numbers from 0.6 to 1.0) increments of lift, pitching moment, and rolling-moment were produced in the correct direction over most of the angle-of-attack range tested. At an angle of attack of 0 deg the servovane control gave a higher incremental lift coefficient and had a more forward location of center of pressure of lift than a comparable flap-type control. The servovane control tested was subject to rather severe vibrations.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1956
- Accession Number
- ADA377464
Entities
People
- Robert F. Thompson
- William H. Phillips
Organizations
- National Aeronautics and Space Administration