qHelicopter Specifications for Trim

Helicopter.Item Nbr	Airfoil data:	Nbr. of blades: [bb]	Chord: [cc]	Radius: [R]	Blade Cutout Ratio: [x0]	Twist Type	Theta_o	Theta1	Theta_t	AlphaL0	Rotor Configuration	Ctr-Ctr	Load	Engine Nbr	Engine Count	Seats	Item Nbr:	PartName	Description:	Weight:	qq	gammac	Helicopter Pitch Angle: [Theta]	Angle of Attack - TPP: [alphaTPP]	RRPM:	Ratio	Loss	ff	Vertical Drag: [DV]	Helicopter.Notes	Taper: [cct]	gg	Angle	ds	1st Harmonic of Long. Flapping: [as1]	1st Harmonic of Long. Flapping: [bs1]	a0	Moment Arm: [llP]	Moment Arm: [yyP]	Height above Center of Gravity: [hhP]	Moment Arm: [llS]	Moment Arm: [yyS]	Height above Center of GRavity: [hhS]	Incidence of main rotor shaft: [ii]	Rotor H-force: [Ha1S]	Thrust (Port): [TP]	Thrust (Starboard): [Ts]	Airfoil	Span: [bbH]	Root Chord: [crH]	Tip Chord: [ctH]	Taper Ratio: [lamdaH]	Sweep Angle of Mid-chord Line: [Lambdacover2H]	Aspect Ratio: [ARH]	Incidence: [iiH]	Moment Arm: [ llH]	Height above C.G.: [hhH]	Horizontal Distance from Main Rotors: [xoverRH]	Vertical Distance from Main Rotors: [zprimeover RH]	Zero Lift Angle of Attack: [alphaLOH]	Slope of LIft Curve: [aaH]	Downwash angle induced by main rotor: [epsolonMH]	Downwash angle induced by fuselage: [epsolonFH]	Dynamic Pressure Ratio: [qHoverq]	Rotor Downwash Ratio: [vHoverv1]	Fuselage Downwash Ratio: [depsilonF/dalpha]	Span Efficiency Factor: [deltaiH]	Zero Lift Drag Coefficient: [CDOH]	Airfoil:	Area: [AV]	Span: [bbH]	Root Chord: [crH]	Tip Chord: [ctH]	Taper Ratio: [lamdaH]	Sweep Angle of Mid-chord Line: [Lambdacover2H]	Aspect Ratio: [ARH]	Horizontal Distance from Main Rotors: [xoverRH]	Vertical Distance from Main Rotors: [zprimeover RH]	Zero Lift Angle of Attack: [DeltaalphaLOH]	Downwash angle induced by main rotor: [epsolonMV]	Downwash angle induced by fuselage: [epsolonFV]	Moment Arm: [ llV]	Height above C.G.: [hhV]	Length: [LF]	Width: [WF]	Height: [HF]	Wetted Area: [SWF]	Volume: [VF]	Fineness Ratio: [FRF]	Height above C.G.: [hhF]	Height above C.G.: [hhF]	Downwash angle induced by main rotor: [epsolonMF]	Efflux Volume: [VE]	Moment Arm: [ llE]	Height above C.G.: [hhE]	Fuel Tank Capacity:	Pitch: [Iyy]	Roll: [Ixx]	Yaw: [Izz]	Engine.Item Nbr	Make:	Model:	Bore	Stroke	Displacement:	Power:	Power-RPM	Torque:	Torque-RPM	Run-RPM	Bare weight:	Extras	Engine.Notes
847	VR-7	6	0.4917	8	0.25	2	0	-6	0	-1.4	3	0	332	282	1	1	847	Inside - Intermeshing UniCopter I - 1-seat	Absolutely Rigid Rotor. No teetering or lead-lag hinges. Only feathering .	385	1	0			643	7	4	4			0.375	0	9	2.25	0	0		0	-13.5	0			13.5	0				NACA 0012	4	1	0.5				3.6			7.667	2.4	0	0.06	0	0	1	2	1		0.006	NACA 0015										0																					282	Hirth	F-30 2 85hp			1042	85	5500	78	4500	4500	96	9	I have guessed at weight brake-down. Fuel Injected.