Hi there, I just checked Janes' All the world aircraft (versions 1979-1880 and 1989-1990) which confirms the data found in Prouty, except for the main rotor blade twist. For thi,s Janes gives a value of -14 degrees, but this value is probably measured from the root cutout (so not from the centre of the hub as in Prouty).
Performance data (ISA, T/O weight: 25400 kg) for the CH-53E: - Max level speed @ S/L: 170 kts (315 km/h; 196 mph) - Cruising speed @ S/L: 150 kts (272 km/h; 173 mph) - Max Rate of Climb @ S/L: 838 m (2750 ft) / sec - Hovering ceiling IGE max power: 3520 m (11550 ft) - Hovering ceiling OGE max power: 2895 m (9500 ft) - Service ceiling max cont power: 5640m (18500 ft) - Range (optim cruise speed for best range): 1120 nm (2075 km; 1290 miles) Powerplant 3 T64-GE-415 or T64-GE-416 turboshaft engines; - performance each: - max rating: 3266 kW (4380 shp) 10 minutes - intermediate rating: 3091 kW (4145 shp) 30 minutes - max cont rating: 2756 kW (3696 shp) - rotor transmission: - rated @ 9792 kW (13140 shp) for 10 sec - rated @ 8627 kW (11570 shp) for 30 min Fuel capacity: - self-sealing bladder fuel cell in forward part of each sponson, each w. capacity of 1192 litres (315 US gallon) - additional 2-cell unit, capacity 1465 litres (387 US gall), -> total standard internal capacity: 3849 litres (1017 US gall) - optional drop tanks outboard of each sponson for CH-53E, total capacity 4921 litres (1300 US gall) MH-53E can carry 7 internal range extension tanks, total capacity 7949 litres (2100 US gall) Weights: - empty: 15 071 kg (33 226 lb) - internal payload (100 nm radius): 13 607 kg (30 000 lb) - external payload (50 nm radius): 14 605 kg (32 200 lb) - MTOW: 33 339 kg (73500 lb) Rotor dimensions: - MR diameter: 24.08 m - TR diameter: 6.10 m - MR blade chord: 0.76 m - MR blade twist: 14 deg Greetings, Wim On 12/18/06, wim van hoydonck <[EMAIL PROTECTED]> wrote: > Hi there, > > > Some data for the CH53e yasim model, taken from Prouty [1], p. 699. > > Looking at the data in cvs, rotor diameters and chords should/could be > changed, just like control input ranges for the main and tail rotor. > > > Weights (lb): > - Empty: 33009 > - MTOW (internal payload): 69750 > - MTOW (external payload): 73500 > - Fuel capacity (norm): 6682 > - Fuel capacity (aux): 8450 > > Engines: > - Type: General Electric T64-GE-416 > - Number: 3 > - Max T.O. rating: 13140 > - Max usable power: 11570 > > Rotor Parameters: Main Tail > - Radius (ft): 39.5 > 10 > - Chord (ft): 2.44 > 1.28 > - solidity 0.138 > 0.163 > - No. of blades: 7 > 4 > - Tip speed (ft/sec): 732 > 733 > - twist (deg): -20 > -8 > - equiv. linear hinge offset ration (e/R): 0.063 0.043 > - Airfoil: SC1095 > NACA 0015 > - Collective range (deg): -1.4 to 19.6 -10 to > 24 > - Longitudinal cyclic range (deg): -8.5 to 18.0 - > - Lateral cyclic range (deg): -9.8 to 6.1 - > - Polar moment of inertia (slug ft^2) 51800 181 > > > Greetings, > > Wim > > > [1] Prouty, R. W., Helicopter Performance, Stability and Control > > > -- > Avoid hangovers - stay drunk! > -- Avoid hangovers - stay drunk! ------------------------------------------------------------------------- Take Surveys. Earn Cash. Influence the Future of IT Join SourceForge.net's Techsay panel and you'll get the chance to share your opinions on IT & business topics through brief surveys - and earn cash http://www.techsay.com/default.php?page=join.php&p=sourceforge&CID=DEVDEV _______________________________________________ Flightgear-devel mailing list Flightgear-devel@lists.sourceforge.net https://lists.sourceforge.net/lists/listinfo/flightgear-devel
