| Helicopter Disk and Power Specifications |
| Item Nbr: | 474 | Friday, July 14, 2000 | 11:01:11 PM |
| Black is input. | Blue is calculated. |
| Test Conditions: |
| Collective Pitch: (used for Flight - Hovering w/ Blade Element Theory) | 11.97 | deg |
| Forward Speed: (used for Flight - Forward w/ Momentum Method) | 70 | knots |
| Rate of Vertical Climb: (used for Flight - Vertical w/ Momentum Method) | 250 | ft/min |
| Weight: |
| Empty Weight: [EW] | 1679 | lb. |
| Payoad: [Load] | 523 | lb. |
| Gross Weight: [GW = EW + Load] | 2202 | lb. |
| Rotor: |
| Blade: |
| Type of airfoil | NACA 23017 |
| Angle of attack for zero lift [AlphaL0] (0 for 0012. >0 for cambered) | -1.4 | deg. |
| Number of blades: [bb] | 4 |
| Radius: [R] | 19.675 | ft. |
| Chord: [cc] | 0.9583 | ft. |
| Blade Area: [Ab]=[bb*cc*R] | 75.42 | sq-ft |
| Aspect Ratio: [R / cc] | 20.53 | :1 |
| Blade cutout ratio: (The blade root radius divided by the tip radius.) | 0.15 |
| Taper (not used at present) [cct] |
| Twist Type; 1 - none; 2 - linear; 3 - ideal. | 2 |
| Pitch that the blade would have if extended into center of rotation. | 0 | deg. |
| Angle of twist (washout). Tip pitch - root pitch. i.e.negative value. | -4 | deg. |
| Pitch at the blade tip: [Theta_t] (for ideal only) | 0 | deg. |
| Hub(s): |
| Configuration: Single=1, Coaxial=2, Synchropter=3, Side-by-side=4 | 3 |
| Center to center distance between twin rotor shafts: [Ctr-Ctr] | 0.00 | ft. |
| The vertical distance between twin rotor hubs: [Gap] | 0.00 | ft. |
| The angle of each mast off of vertical Re synchropter: [Angle] | 12.00 | deg. |
| The horizontal distance between twin rotor hubs: [Stagger] | 1.93 | ft. |
| Disk: |
| Disk area (1 rotor); [A1] | 1216.13 | sq-ft |
| Total disk area: [AT] | 1292.16 | sq-ft |
| Effective disk area: [A] | 1694.78 | sq-ft |
| Rotor solidity ratio: [Sigma] = [Ab] / [A] | 0.05837 | % |
| Speed: |
| RPM of Rotor: [RPM Hub] | 182 | rpm |
| Tip speed: [Omega_R] | 374.99 | ft/sec |
| Tip mach number: [TipM] | 0.34 | % M1 |