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Revolver

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« Reply #105 on: August 21, 2015, 07:13:55 am »

Hi Simon,

how can I be help...

BR,
Stefan
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bomber

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« Reply #106 on: August 21, 2015, 07:22:45 am »

Hi Stefan,

If you look at the pilots handbook.pdf within the docs folder of the Ask-13 download, there's various diagrams showing the CoG and centre of lift positions and the dimensions froma reference point. This being the front spar whch is also equal to the rear pilots position...

I'd like someone to do some maths and determine the location of the CoG (based on 2 pilots) and the cente of lift and thus the static margin and if the centre of lift is infront or behind the CoG...

Yes I've done this myself but would like some cross checking on it..

Regards

Simon
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Revolver

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« Reply #107 on: August 21, 2015, 07:57:31 am »

Hmm ... either I am blind, or I do not know what you talking about ... where can I find this PDF-File?  Please give me a direct link to it. Thank's.
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bomber

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« Reply #108 on: August 21, 2015, 08:33:02 am »

at work at present will do so once home...

thanks

Simon
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bomber

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« Reply #109 on: August 21, 2015, 03:53:51 pm »

my apologies looks like I didn't include this folder in the download... oops

pages 17 18 & 19

can you determine the location of the CoG
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Revolver

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« Reply #110 on: August 21, 2015, 05:01:37 pm »

Quote

Sorry, but the page you were trying to view does not exist.

and Manual is entirely in English, so what should I translate it?

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bomber

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« Reply #111 on: August 25, 2015, 01:43:13 pm »

It's not a simple translation I need but a confirmation of where I'm working out the CoG of the plane to be under a 2 man situation.

It might be that I have to contact a gliding club with regards this plane..
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Revolver

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« Reply #112 on: August 25, 2015, 04:04:08 pm »

I honestly do not know what you do not understand.
So if I have understood correctly, then there is no fixed number. For whatever reason.
It could most probably be because the pilot has an adjustable seat, or the glider has the Different
empty weight. The MIN and MAX numbers are already entered in table, so you need not to be expected.
As an an example:

GL = 280kp
min-490mm
max-545mm

So, difference - 55/2 = 27.5 (with MIN+MAX)

R=CoG

In these new documentaries the table has been extended even to 2 (330-340) further figures.

BR,
Stefan

p.s. see page-10 & 11...
« Last Edit: August 26, 2015, 07:29:58 am by AH-DG »
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FarlanderMiG

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« Reply #113 on: August 26, 2015, 02:40:37 pm »

Not able to access my home computer. Is ridge lift from wind a thing now?
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bomber

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« Reply #114 on: August 26, 2015, 04:25:31 pm »

I don't think ridge lift as it's more about an upward moving airstream following deflection...

however.... if we talk about the basics of ridge lift there might be a solution especially as there's google maps integral to the application.
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bomber

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« Reply #115 on: August 26, 2015, 04:30:48 pm »

I honestly do not know what you do not understand.
.
.

GL = 280kp
min-490mm
max-545mm

So, difference - 55/2 = 27.5 (with MIN+MAX)

R=CoG

So Stefan... from the diagrams you're saying the CoG is min 490, max 545mm towards the tail measure from the front wing spar ?

trust me we're getting there..

Simon
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Revolver

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« Reply #116 on: August 26, 2015, 05:36:38 pm »

Simon, according to the drawing (ASK-13 Balancing sheet) - YES.
So, G1 to G2, as GL is in the case = empty weight.
In the page -10/11 is told about it. Therefore, if you want to have
an absolute point-0(CoG), you must still be divided by 2, the 2-figures.
I see it so ...
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FarlanderMiG

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« Reply #117 on: August 27, 2015, 02:46:50 pm »

So what are you guys looking for? The best possible CoG for the particular plane? or just the allowed "area"?
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