As part of the NASA/Navy Abrupt Wing Stall Program, a relatively low-cost, rapid-access wind-tunnel free-to-roll rig was developed. This rig combines the use of conventional models and test apparatuses to evaluate both transonic performance and wing-drop/rock tendencies in a single tunnel entry. A description of the test hardware as well as a description of the experimental procedures is given. The free-to-roll test rig has been used successfully to assess the static and dynamic characteristics of three different configurations--two configurations that exhibit uncommanded lateral motions, (pre-production F/A-18E and AV-8B), and one that did not (F/A-18C).
Development of a Free-to-Roll Transonic Test Capability (Invited)
2003
18 pages
Report
No indication
English
Test Facilities & Equipment , Aircraft , Wind tunnel tests , Wind tunnel apparatus , Wind tunnel models , Fighter aircraft , Aerodynamic stalling , Wing rock , Safety management , Aircraft design , Aerodynamic configurations , Lateral control , Aerodynamic brakes , Reliability analysis , Risk , Experiment design
DEVELOPMENT OF A FREE-TO-ROLL TRANSONIC TEST CAPABILITY (Invited)
British Library Conference Proceedings | 2003
|Development of a Free-To-Roll Transonic Test Capability
AIAA | 2003
|Development of a Transonic Free-To-Roll Test Capability
AIAA | 2004
|ABRUPT WING STALL-PART 1 - Development of a Transonic Free-to-Roll Test Capability
Online Contents | 2004
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