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.
A Report on Stability and Control Testing of a Tilt Wing V/STOL Aircraft
Sae Technical Papers
National Aeronautic Meeting and Production Forum ; 1966
01.02.1966
Aufsatz (Konferenz)
Englisch
Report on stability and control testing of tilt wing V/STOL aircraft
Engineering Index Backfile | 1966
|Forward Swept Tilt Wing V/STOL Aircraft
British Library Conference Proceedings | 1997
|Forward Swept Tilt Wing V/STOL Aircraft
British Library Conference Proceedings | 1997
|Cyclic Pitch Control on a V/STOL Tilt Wing Aircraft
NTIS | 1971
|Design aspects and flight testing vertol 76 tilt-wing VTOL/STOL research aircraft
Engineering Index Backfile | 1958
|