Good Conventional attempt

Size of the vortex is pressure differential=Lift=weight (In level Flight)

In level flight it is only weight dependent, High speed low CL but Higher Speed=Same pressure differential, therefore the size of the vortex will remain same irrespective of the speed


great attempt

@rcpilotacro,
Thanks for the kind words, even though i skipped my first answer (which was correct) in favour of my second answer (incorrect).
No one else has responded, except for rastsaurabh, whose criptic one word post 'read', was presumably for me, as it couldn't have been for you!
Hence query to saurabh,

@rastsaurabh,
Please recommend reading list...
Regards.

Iyer sir ....
Gusty is the best to suggest any reading.
If i could suggest any reading or knowledge it would be Mobile technology.
Just neglect my post. Btw it was meant that your post was seen before you could correct.

interesting discussion on funjet ultra roll charecteristics

http://www.rcindia.org/electric-planes/funjet-ultra-6s-300kmph-build-and-maiden-flight/msg244169/#msg244169

Quote from: rcpilotacro on December 09, 2010, 08:07:41 PM
pulled out from my other post. Pruned it a little. To make understanding of RC flying clear.

firstly in level flight weight= lift =CL ½ σ V² S. CL is coefficient of lift, which depends on your wing angle of attack (position of the nose in level flight) shape, camber etc, ½ σ V² is called the dynamic pressure, simply put, number of air molecules for a given time, ALSO CALLED THE INDICATED AIRSPEED, 'S' is your wing area.

Now, aeroplane has lift and weight acting as one couple (noseup or down will in RC language, will depend on the cg, because weight acts along it, and position of wings because centre of pressure through which the lift acts).

It also has thrust and drag couple acting on it. nose up or down will depend on position of your engine and wings, which if you are not designing, is pretty much taken care of,

Couple of Forces. For aeroplane to fly in level unaccelerated flight all these couple have to balance so that the residual is zero. If the aeroplane is say designed to get airborne at 30 kmph, it will get airborne at 30 kmph, if the wind that is blowing is 30 kmph, the ground speed at which will get airborne will be zero. But remember the thrust drag couple will have to be zero, which means, you have to open power normally as you do in nil wind condition. If the winds are 40 kmph the aeroplane after getting airborne into wind will travel rearward at 10 kmph. With respect to ground, however with respect to air it is still travelling at 30 kmph. Bottom line CL and S being same it is the ½ σ V² (the number of air molecules for a given time above and below the wings) which matter.

Much Appreciated