UniCopter Characteristics
Overview:
XX:
General:
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3-blade Rotors ~ Item 0847 |
4-blade Rotors ~ Item 0862 |
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Item Number = |
0847 |
0862 |
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Seats = |
1 |
1 |
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Fuel Tank Capacity = |
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Parasitic Drag Area [ff] = |
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CG of Origin:
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Longitudinal Distance:[llG] |
xx" |
1.26" |
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Lateral Distance: [yyG] |
0" |
0" |
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Vertical Distance: [hhG] |
" |
24.5" |
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Trim Conditions:
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Helicopter Pitch Angle: [Theta] |
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Helicopter Role Angle: [Phi] |
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Angle of Attack - TPP: [alphaTPP] |
Flight Condition:
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Dynamic Pressure: [qq] |
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Angle of Climb: [gammac] |
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Sideslip Angle: [Beta] |
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Miscellaneous:
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Vertical Drag: [DV] |
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Vertical Distance from Main Rotors: [zprimeover RH] |
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Downwash angle induced by main rotor: [epsolonMV] |
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Downwash angle induced by fuselage: [epsolonFV] |
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Engine:
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Engine Number: |
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Make: |
Lycoming |
Lycoming |
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Model: |
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Speed [Run-RPM]: |
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Engine Count: |
1 |
1 |
Power-Train:
See;|
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Ratio - Total: |
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Loss - Total: |
Weight:
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Empty: |
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Load: |
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Gross: [GW] |
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Aircraft Inertia:
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Pitch: [lyy] |
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Roll: [lxx] |
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Yaw: [lzz] |
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Propeller:
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Radius: [PProp] |
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Number of Blades: [bProp] |
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Maximum RPM: [RPMProp] |
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3-blade Rotors ~ Item 0847 |
4-blade Rotors ~ Item 0862 |
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Number of Blades: [bb] = |
Total of 6 |
Total of 8 |
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Radius: [R] = |
9'-6", 114"; plus radiused tip. |
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Disk Area (1 rotor): [A1] = |
283.53 ft2 |
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Total Disk Area: [AT] = |
330.89 ft2 |
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??? |
Effective Disk Area: [A] = |
406.95 ft2 |
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Disk Loading: [DL] = |
3.4755 lb/ft2 |
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Rotor Solidity Ratio: [Sigma] = |
0.1939 |
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Speed: [RRPM] = |
480 rpm |
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Speed: [Omega] = |
50.265 rad/sec |
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Tip Speed: [Omega_R] = |
477.52 |
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Tip Mach Number: [TipM] = |
0.4277 |
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Thrust (Port): [TP] = |
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Thrust (Starboard): [TS] = |
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Polar Moment of Inertia: [J] = |
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Pre-cone Angle: [aP] = |
3º |
3º |
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Moment Arm: [llP] = |
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Moment Arm: [yyP] = |
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Height above CG: [hhP] = |
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Moment Arm: [llS] = |
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Moment Arm: [yyS] = |
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Height above CG: [hhS] = |
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Rotor Configuration: = |
Intermeshing |
Intermeshing |
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Obliquity: [Angle] = |
9º |
9º |
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Stagger: [ds] = |
29" ??? |
29" ??? |
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Airfoil Data: = |
NACA 00xx |
NACA 00xx |
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Profile: = |
Airfoil changes from 0006 at tip to approximately 0012 at 42% of R., to thicker 00xx toward hub. |
Airfoil changes from 0006 at tip to approximately 0012 at 42% of R., to thicker 00xx toward hub. |
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Chord at root: [cc] = |
1.667 ft ??? |
1.667 ft ??? |
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Taper: [cct] = |
The blade tapers from 14.5" at 48" r to 7" at 114" r R. This is a taper of 1.364" per ft. There is also an opposite taper from 12" at 6" r to 14.5" at 48" r. I wonder what this would be in a so-called as an equivalent taper? |
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Chord at Widest Point: = |
14.5257" |
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Chord at Tip: = |
7" |
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Aspect Ratio: [AR] = |
8.4407 ??? |
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Blade Cutout Ratio: [x0] = |
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Twist Type: = |
Independent Root & Tip Control (IRTC), Active Blade Twist (ABT) |
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Twist: [Theta1] = |
The blade has no twist so that one mold can produce all six 'initial' blades. ??? |
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AlphaL0: = |
0º |
0º |
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Blade-flapping Inertia: [IB] = |
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Lock no.: [gamma] = |
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Blade Area: [BL] = |
6 x 9 sq-ft = 54 sq-ft. ??? |
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17.926 lb/ft2 ??? |
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Rotor Solidity Ratio: = |
0.1939 ??? |
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Pitch at Mast: [Theta_o] = |
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Pitch at Tip: [Theta_t] = |
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Tip: The slope back may allow for the feathering axis to be a little further aft plus reduce the tip vortex ??Move?? |
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XX:
Fuselage:
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3-blade Rotors ~ Item 0847 |
4-blade Rotors ~ Item 0862 |
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Length: [LF] |
xx |
xx |
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Width: [WF] |
xx |
xx |
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Height: [HF] |
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Wetted Area: [SWF] |
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Volume: [VF] |
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Fineness Ratio: [FRF] |
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Drag infront of Origin: [llF] |
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Drag below Origin: [hhF] |
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Downwash angle induced by main rotor: [epsolonMF] |
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Vertical Stabilizer:
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Number: |
2 |
2 |
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Airfoil: |
xx |
xx |
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Span: [bbH] |
xx |
xx |
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Root Chord: [crH] |
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Tip Chord: [ctH] |
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Zero Lift Angle of Attack: [DeltaalphaLOH] |
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Moment Arm: [ llV] |
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Height above C.G.: [hhV] |
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Taper Ratio: [lamdaH] |
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Sweep Angle of Mid-chord Line: [Lambdacover2H] |
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Aspect Ratio: [ARH] |
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Horizontal Distance from Main Rotors: [xoverRH] |
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Area: [AV] |
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Horizontal Stabilizer:
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Number: |
1 |
1 |
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Airfoil |
xx |
xx |
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Span: [bbH] |
xx |
xx |
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Root Chord: [crH] |
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Tip Chord: [ctH] |
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Taper Ratio: [lamdaH] |
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Sweep Angle of Mid-chord Line: [Lambdacover2H] |
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Aspect Ratio: [ARH] |
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Incidence: [iiH] |
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Moment Arm: [ llH] |
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Height above C.G.: [hhH] |
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Horizontal Distance from Main Rotors: [xoverRH] |
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Vertical Distance from Main Rotors: [zprimeover RH] |
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Zero Lift Angle of Attack: [alphaLOH] |
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Slope of LIft Curve: [aaH] |
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Downwash angle induced by main rotor: [epsolonMH] |
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Downwash angle induced by fuselage: [epsolonFH] |
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Dynamic Pressure Ratio: [qHoverq] |
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Rotor Downwash Ratio: [vHoverv1] |
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Fuselage Downwash Ratio: [depsilonF/dalpha] |
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Span Efficiency Factor: [deltaiH] |
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Zero Lift Drag Coefficient: [CDOH] |
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Area: [AH] |
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Last Revised: October 24, 2005