This paper presents recent results from a cooperative effort by the U.S. Army Aeroflightdynamics Directorate, the Technion Israel Institute of Technology, and Northern Arizona University to study and simulate the behavior of the 6 × 6 × 8 ft CONEX cargo container in forward
flight suspended beneath a UH‐60 Black Hawk helicopter. This load, like other cargo containers, is subject to massively separated unsteady flow and is limited by stability to operational airspeeds well below the power‐limited speed of the configuration. The study makes use of
aerodynamic data from wind tunnel, flight test, and computational fluid dynamics. The objective is a simulation of the helicopter‐slung load system validated over the complete flight envelope. The principal remaining technical challenge is a model of the unsteady load aerodynamics capable
of predicting the critical unstable speed. Some progress has been made in meeting this challenge.
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Document Type: Research Article
San Jose State University Foundation, Aeroflightdynamics Directorate, Moffett Field, CA
Publication date: 2009-07-01
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