I just noticed that there might be/is a typo in the ch53e-yasim.xml file. change: ground-effect-constatnt="1.25" to: ground-effect-constant="1.25"
Greetings, Wim On 1/3/07, wim van hoydonck <[EMAIL PROTECTED]> wrote: > 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! > -- 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
