Hi Maik,
Once our library opens again next year (they are moving to a new building), I'll cross check that data with Janes (I work at the faculty of aerospace engineering in Delft). > Very surprising for me are the > cyclic/ collective data with approx 20+18=38 degree maximum incidence of > the main rotor. That's the maximum pitch angle at the root of the blade which is not the same as the angle of attack of a blade (element) along the span of the blade (inflow induced by the rotor itself reduces the angle of attack). You would only need that combination in high speed forward flight, which in normal flight is limited by the stall on the inner side of the retreating blade. > Unfortunately I do not have any information about the > airfoil (SC1095). This ([1]) NASA report contains some data about wind tunnel test done with that airfoil. > One important point: the main rotor and the tail rotor > are twisted. Do you know, where the incidence is measured? Pitch angle (theta) is normally measured from the root of the blade, as can be seen in [2], page 322. Flight path angle (phi) is calculated from the tangential and normal velocity components at a blade element and the angle of attack (alpha) is the difference between (or sum of) these two (depending on the choice of positive axes). > Do you have such data for other helicopters in your book (bo105 (but > here the actual data should be correct), ec135, ec145, ch47d, s76c, > little nellie)? I have access to the majority of editions of Janes All The Worlds Aircraft between 1976 and 2006, so yes :) (although I'm not sure about little nellie ...) Greetings, Wim [1] http://halfdome.arc.nasa.gov/publications/files/NASA-TP-2003-212265.pdf [2] http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19960054374_1996092848.pdf On 12/18/06, Maik Justus <[EMAIL PROTECTED]> wrote: > Hi Wim, > > very interesting data. I have googled to find out, which values are > correct, at least for the rotor diameter there is many data on the net. > It seems, that in the version in cvs some data are from the ch53d (or > are there different ch53e variants?). Very surprising for me are the > cyclic/ collective data with approx 20+18=38 degree maximum incidence of > the main rotor. Unfortunately I do not have any information about the > airfoil (SC1095). One important point: the main rotor and the tail rotor > are twisted. Do you know, where the incidence is measured? > > Do you have such data for other helicopters in your book (bo105 (but > here the actual data should be correct), ec135, ec145, ch47d, s76c, > little nellie)? > > Thank you, > Maik > wim van hoydonck schrieb am 18.12.2006 15:49: > > 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 > > > > > > > > > ------------------------------------------------------------------------- > 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 > -- 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
