Item 1081
OTHER: Dynamics -
Trim - Sideforce, Yawing and Rolling Moments
Notes:
The rolling moment of the fuselage due to sideslip is caused by its
dihedral effect and can be either slightly positive or slightly negative. A method for estimating this moment using the physical parameters of the fuselage an wing is given in [Hoak, 'USAF Stability and Control Datcom" ASAF DATCOM. 1960]. [Source ~ RWP1 p.513] This is for airplanes and is not very applicable to the helicopter because of the influce of the main rotor wake on the tail rotor and the vertical stabilizer.My thought only; is that this may be valid for the intermeshing configuration because of the symmetry of downwash and the lack of a tail rotor.
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Last Revised: May 5, 2002