0916

Item 0916

DESIGN: UniCopter ~ Trim, Stability & Control - Trim - Vertical Stabilizer

Symbol Definitions - Flight Dynamics

Forces on Vertical Stabilizer (and two Winglets?):

For calculation on the area of the vertical stabilizer [A_V] see: Dimension & Area - View - Side (X-Z plane)

More code to go here; see Horizontal above and page 504 +

L_V = A_V * C_LV

D_V = A_V * [(C²_LV/ (π * AR_V )) * (1 + δ_{i V}) + C_{D0 V} ]₊D_VINT

The dynamic pressure ratio [(q_V /q) * q] will be 1 since the vertical stabilizer is not in the effects of the rotors or fuselage. It has therefor been removed from the above equations.

	X_V =	-D_V cos(β)*
	Y_V =	- D_V sin(β)*
	Z_V =	X_V sin(Θ - γ_c)*

The sidewash angles of [η_PV + η_SV + η_FV] have been removed from the above equations since they will be zero in all conditions. A possible exception is autorotation but even in this condition, the outer portion of the rotor disks is driving air downward and away from the tail.

The downwash angles of [ε_PV + ε_SV + ε_FV] ] have been removed from the above equations since they will be zero in all conditions.

The lift [- L_V * sin(β)] & [L_V * cos(β)] has been removed from the X and the Y equations

Notes:

Note

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Last Revised: May 8, 2002