Explanatoin of .par words

[jon]

Hi out there.

I'm having some problems understanding some of the words used i the .par files.
Is it someone who understands and can explain the meaning of the ?words? to me
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?camax? des Hauptflügels ?camax? of main wing
?camin? des Hauptflügels ?camin? of main wing
Auftriebsanstieg The way it rises, gets lift/up
?dcaue? ?dcaue?
cw0 des Hauptflügels Value of resistance/drag of main wing
Widerstandsbeiwert des Rumpfes Value of resistance/drag of fuselage
?mue?Boden ?mue? underside
?mcwue? ?mcwue?
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I prefer english please.
??? ???

[Sturdy Birdy 10]

Jon
i had the same problem before. i found a cheap way to change it to english. go to
[URL=http://www.google.com/language_tools?hl=en]
scroll down in this page untill you see a big box with the words Translate. Copy the words into the small box under the word translate. then where it may say translate from german to english choose from which language to what language you want to change it.
(if it is a website)
scroll a little down where it say Translate web page put in the web url and then click tranlate and there you have it.

[jon]

Hi.

I think it is a little more tecnical than that, however the link helped out so far.
It brought me to a site with another translated explanation, an by merging it with the one I had it made more sense.

The merged result looked like this:

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Value Explanation Explanation of the explanation
0 iModelType: 0 = Flugzeug speaks for itself 1= Heli 0 = Plane
9 Motorkraft: Schub in Newton should speak for itself too; motortrust, the power in Newton
0.35 Seitenruderausschlag in rad the movement/deflection of the rudder; try some different values
0.16 Max. Hoehenruderausschlag in rad movement/deflection of the elevator
0.000 Querruderausschlag (Flügelverwindung) in rad movement/deflection of the ailerons
1.15 ca max des Hauptflügels the maximum of lift the wing can take
-0.3 ca min des Hauptflügels the minimum of lift the wing can take (important for flying upside-down!)
6.2 Auftriebsanstieg The way it rises, gets lift/up
2.0 dcaue How will it perform in stall.
The value of lift ca raises with dca every rad angle of attack, until it reaches camax.
At that point it will fall with dcaue (pro rad angle of attack) until it reaches 0. The same will happen when ca camin comes below the value in the opposite direction.
The higher the value, the more extreme the stall-point and the reaction of the plane as soon as the lift disappears.
The drag in case camax and/or camin are not exceeded or 'under-stepped' is cw0. In case these values are exceeded the drag will rise with dcwue pro angle of attack.
0.008 cw0 des Hauptflügels from Werner:
The drag-value from the mainwing(s) with 0 degrees angle of attack.
"Momentenbeiwert des Hauptflügels": defines the roll-performance of the wings around the longitudinal axis. In a "normal" plane the profile of the wings would cause the plane to move around the longitudinal axis and drop its nose down, when the stabilo isn't stabilising it. With a full-symmetric profile is the 'Momentenbeiwert' 0.0 (see NOLIMIT). A flying wing needs in fact a positiv 'Momentenbeiwert' to fly stable.
0.002 Widerstandsbeiwert des Rumpfes As much drag the fuselage can take (the GeeBee takes more as an ASW27
0.5 mueBoden Rolling-resistance of the ground. This means that this value will be bigger by flying from a sandy soil, than when taking of from a paved runway. A value of 1.4 will cause the model to move hardly anymore (like Schlamm after fresh rain without frost
J. Hansen (Webmaster from LSC-Condor e.V. Berlin)
1.4 mcwue The behaviour in stall-situation. The value of lift ca rises with dca pro rad angle of attack until it reaches camax. Then it falls with dcaue (pro rad Anstellwinkel too) until it reaches 0. The same will happen when ca camin will be under-stepped simply in the other direction. The higher the value, the more extreme the performing of the stall, as soon as the lift droppes to 0.
The value of the drag is, in case it doesn't rise above or below camax, cw0. If one of these values will be exceeded, the drag will rise with dcwue pro rad angle of attack.
-0.09 Momentbeiwert des Hauptflügels Stalling point main wing (moment of inertia?)
0.06 Anstellwinkel des Hauptflügels gegenüber dem Rumpf in rad angle of attack (main wing in comparison with fuselage) in rad
4.000 Spannweite des Hauptflügels in m wingspan (of mainwing) in meters
0.21 Flaechentiefe des Hauptflügels in m Wing cord in meters
0.090 Schwerpunktrücklage von der Vorderkante des Hauptflügels in m Point of CG, distance from frontside main wing in meters; the further to the back, the sooner it will fall aside
1.9 Masse des Modells in kg Weight of the model in kilograms
0.16 Trägheitsmoment um die Hochachse Moment of inertia yaw/vertical axis (rudder)
0.099 Trägheitsmoment um die Querachse Moment of inertia pitch/lateral axis (elevator)
0.08 Trägheitsmoment um die Längsachse Moment of inertia longitudinal axis (ailerons)
0.094 Fläche des Höheleitwerks in qm Area/surface of elevator in square meters
0.028 Fläche des Seitenleitwerks in qm Area/surface of rudder in square meters
0.838 Leitwerkshebel in m Distance wings - tailsection in meters
0.004 V-Form Faktor V-degree of main wing
0.162 Flugzeughöhe (für Grafik) to determine the exact position of the wheels on the surface (to prevent the wheels from disappearing in the ground, or floating somewhere in the air

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Copy it to a table in a Word doc, and work it out from there.
Maybe this can be helpful for some others too.

By the way, I noticed that there is some different translatoins in different websites. Could it be an idea to get one only on the homepage of RC-sim