Dynamic Behavior of Angle-of-Attack Vane Assemblies.
Abstract
A relatively simple analytic model was developed for predicting the dynamic behavior of angle-of-attack vane assemblies in response to changes in the free stream direction and/or to transverse motions of the vane's pivot axis. Experimental tests of a typical vane were performed in five-foot, low subsonic wind tunnel. Comparisons were made of the model's predictions with these tests and with other test results found in the literature. Viscous and tip effects were not included in the model. Viscous and tip effects were not included in the model. The aerodynamic damping was experimentally found to be essentially independent of airspeed as predicted, but the model's estimates were only within a factor of 2 to 3 of the data. It was found that typical aircraft instrumentation boom motions may lead to significant errors in the apparent angle of attack.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1974
- Accession Number
- ADA011604
Entities
People
- James T. Karam Jr
Organizations
- Air Force Institute of Technology