Accession Number:

ADA383536

Title:

Control-Surface Deflection Effects on the Innovative Control Effectors (ICE 101) Design

Descriptive Note:

Final rept. 1 Oct 1998-30 Sep 1999

Corporate Author:

AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE

Report Date:

2000-03-01

Pagination or Media Count:

200.0

Abstract:

A static wind tunnel test of the Innovative Controls Effectors ICE 101 conceptual aircraft configuration was conducted in the Air Force Research Laboratorys Vertical Wind Tunnel. This entry characterized the increments to the aerodynamic loading provided by the various control surfaces while using a more finely-resolved test matrix in angle of attack and sideslip than typically seen in wind tunnel testing. The purpose for obtaining these data was to determine the effect which control surface deflection had on critical state locations in preparation for the test of a second ICE model built with remotely-actuated control surfaces. Critical states are discrete flight mechanical states where the aerodynamic response looses its analytic dependence on one or more state variables. These data demonstrate that the aerodynamic increments are in many cases at minimum nonlinear functions of the surface deflection angle, and strongly suggest that some critical states do shift in angle of attack andor sideslip with changing deflection angle.

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE