| Test Conditions: |
| Collective pitch: [Theta_o] (used in hover calculation w/ blade element theory) | 3 | deg |
| Forward Speed: [Vfwd] (used in momentum theory) | 55 | knots |
| Rate of Climb: [Vver] (used in momentum theory) | 500 | ft/min |
| Flight - Hovering: |
| Momentum Method |
| Disk Loading: [DL] | 1.52 | lb/ft2 |
| Velocity: [V1hov] (Average of velocities through the disk.) | 17.85 | ft/sec. |
| Power; [P] (see *) (Figure of Merit set to 0.65) | 26.33 | hp. |
| Power Loading: [PL] (for hover ONLY) (see *) | 19.94 | lb/hp |
| Nondimensional Coefficients; |
| Thrust: [CT] | 0.00211 |
| Power: [CP] | 0.00000 |
| CT / Sigma | 0.06230 |
| Combined Momentum and Blade Element Theory w/ Emphirical Corrections |
| Coefficients of:- |
| Thrust: [CTntl] (w/o tip loss) | 0.00232 |
| Tip loss factor: [B] | 0.97 |
| Thrust: [CT] (with tip loss) | 0.00211 |
| Profile; [CQo] | 0.00211 |
| Induced: [CQi] | 0.00004 |
| Torque: [CQ] | 0.00009 |
| Power: [CP] | 0.00000 |
| ROI CQi / Thrust CQi |
| Disk loading: [DL] (calculated using thrust) | 1.5169 | lb/ft2 |
| Thrust Solidity: [CT/Sigma] | 0.06235 |
| [(DL)(CT/Sigma)] |
| Measured power / Calculated power | 0.96 |
| CQ / Sigma | 0.00000 |
| Thrust: [T] (see *) | 525.39 | lb |
| Horsepower: [hp] (see *) | 22.91 | hp |
| * Calculated values are at International Standard Atmosphere (i.e. Sea level & 59 deg F.). |
| Flight - Vertical: |
| Momentum Method |
| Velocity: [V1ver] (Average of velocities through the disk.) | 22.50 | ft/sec. |
| Change in power; [DeltaP] | 12.39 | hp. |
| Change in blade pitch; [DeltaTheta] | 0.03 | deg |
| Combined Momentum and Blade Element Theory w/ Emphirical Corrections |
| Not done. |
| Flight - Forward: |