Question:from the book principle of helicopter aerodynamics
already provided the needed iteration is at part 2.9:...
Question
from the book principle of helicopter aerodynamics
already provided the needed iteration is at part 2.9:
from the book principle of helicopter aerodynamics
already provided the needed iteration is at part 2.9:...
A helicopter with a gross weight of 3,000 lb (1,363.6 kg), a main rotor radius of 13.2 ft (4.0 m), and a rotor tip speed of 680 ft/s (207.3 m/s) has 275 hp (205 kW) delivered to the main rotor shaft. For hovering conditions at sea level, compute:
Given: mon Cal Rome disk loading, W=3000 lb or -(1363-6 kg) rolar radius = 13:2f og um Rover the speed = Urip = 680 Hils (207-3 m/s Power ar5hp (205kw) 1363-6 27-14 kg/m2 I AC 42 Ideal power loading. P=UT Vi = in flow velocity ) 28A 8=1+225 regim3 b Wherer For air, Voz 3-327 mis 27-14 RX1.225 oldan tertentu = 14536.69 kg m/s pa 3-327 x 1363-6 Grueno, Thrust Coefficient I SAU 2 Q= £ Ста 1363-6 x 2 1-225x7x(4) ²x2073)2 1.0 3x103) Torque Coefficient Ca = & S A Vip R Р Power -WQ » (Vrela) 2 PXR РаР 2x 2058 103 8 Ā Usip yr 1225x9x4 , ?yo (207-33 . G.488104 ME C73/2JI (2x S15X104) 3/2 7,48810-4 27 30.057 X/o2 (m/s) Ca = SA Vrie3 @ = 6-24947042 CA