Wind Tunnel Evaluation of Chinook WT-11 Ultra Light (Essais en Soufflerie de l'Avion Ultra-Leger Chinook WT-11).
Abstract
Full scale wind tunnel tests were carried out on the wing and empennage of WT-11 Chinook ultra light aircraft in the NAE 9m X 9m Low Speed Wind Tunnel. This test program was initiated in response to a request from the Canadian Aviation Safety Board, Ottawa, Ont., to determine the aerodynamics of the vehicle and measure the gross structural airloads. The purpose of the program was to establish if there were any unusual characteristics that might have contributed to several accidents involving this design. Aside from considerable distortion of the wing at high dynamic pressures, corresponding to 50 to 60 mph, and considerable aeroelastic effects on lift curve slope and maximum lift coefficient, at these higher dynamic pressures the basic wind does not appear to possess any inherently dangerous characteristics. However, the empennage exhibits some non-linear characteristics that could possibly cause handling qualities problems. The combination of wing stalling characteristics with horizontal tail characteristics could result in large amplitude pitch down at the stall. Keywords: Ultralight aircraft, Private aircraft, Aerodynamic characteristics, and Wing tail configurations.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1986
- Accession Number
- ADA168978
Entities
People
- W. E. Roderick
Organizations
- National Research Council Canada