| Helicopter Specifications |
| Item Nbr: | 285 | Monday, March 06, 2000 | 2:47:39 PM |
| Name: | Indian | Text in black is input. | Text in blue is calculated. |
| Rotor: |
| Blade: |
| Type of airfoil | NACA 0012 |
| Angle of attack for zero lift [AlphaL0] (0 for 0012. >0 for cambered airfoil.) | 0 | deg. |
| Number of blades: [bb] | 2 |
| Radius: [R] | 10.66 | ft. |
| Chord: [cc] | 0.6667 | ft. |
| Blade Area: [Ab]=[bb*cc*R] | 14.21 | sq-ft |
| Aspect Ratio: [R / cc] | 15.99 | :1 |
| Blade cutout ratio: [xo] (The blade root radius divided by the tip radius.) | 0.05 |
| Taper (not used at present) [cct] |
| Twist Type; 1 - none; 2 - linear; 3 - ideal. | 1 |
| Pitch that the blade would have if extended into center of rotation. [Theta_o] | 0 | deg. |
| Angle of twist (washout). Tip pitch - root pitch. i.e.negative value. [Theta1] | 0 | deg. |
| Pitch at the blade tip: [Theta_t] (for ideal only) | 0 | deg. |
| Hub(s): |
| Rotor Configuration: Single=1, Coaxial=2, Synchropter=3, Side-by-side=4 | 1 |
| 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 Used with synchropter: [Angle] | deg. |
| The horizontal distance between twin rotor hubs: [Stagger] | 0.00 | ft. |
| Coning Angle [a0] | 3.00 | deg. |
| Disk: |
| Disk area (1 rotor); [A1] | 357.00 | sq-ft |
| Total disk area: [AT] | 357.00 | sq-ft |
| Effective disk area: [A] | 357.00 | sq-ft |
| Disk loading: [DL] (calculated using gross weight) | 1.48 | lb/ft2 |
| Blade Loading: [BL] | 37.08 | lb/ft2 |
| Rotor solidity ratio: [Sigma] | 0.03982 | % |
| Engine and Power Train: |
| Engine Nbr: (datebase identifier) | 184 |
| Make: | Hirth |
| Model: | 2703 |
| Engine Count | 1 |
| Ratio | 6.23 | : 1 |
| Loss | 6 | % |
| RPM Hub: (Engine operation rpm divided by Ratio.) | 500 | rpm |
| Weight: |
| Empty Weight: [EW] | 254 | lb. |
| Load | 273 | lb. |
| Gross Weight: [GW = EW + Load] | 527 | lb. |