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A Report on Stability and Control Testing of a Tilt Wing V/STOL Aircraft
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English
Abstract
A limited test program is being conducted on a prototype of the Canadair CL-84 tilt-wing V/STOL aircraft to evaluate its stability and control design objectives. The results to date indicate that only very minor modifications were necessary with regard to the flying control criteria previously established through analysis, fixed-base simulator studies, and variable-stability helicopter tests. In general, the qualitative assessment made thus far of the handling qualities of the CL-84 has proven the adequacy of the established criteria for stability and control performance for systems as complex as that of the CL-84.
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Citation
Longhurst, W., "A Report on Stability and Control Testing of a Tilt Wing V/STOL Aircraft," SAE Technical Paper 660315, 1966, https://doi.org/10.4271/660315.Also In
References
- Martin J. F. Michaelsen, O. E. “The Aerodynamic Approach to Improved Flying Qualities of Tilt-Wing Aircraft.” Paper No. 63-484 presented at AIAA/CASI/RAeS Ninth Anglo-American Conference Oct. 16–18 1963
- Stenning T. A. Dolan, J. A. “Lateral/Directional Simulation of the CL-84 V/STOL Aircraft in the Transition Regime.” Paper No. 64-806 presented at AIAA/CASI Joint Meeting, Ottawa, Canada Oct. 26–27 1964
- McGregor, D. M. “Simulation of the Canadair CL-84 Tilt-Wing Aircraft Using an Airborne V/STOL Simulator.” NRC -- NAE Aero. Report LR-435 July 1965