Re: Physicists Wanted for collaboration


atxinter@xxxxxxxxx wrote:
I am looking for physicists and engineers to collaborate with in
researching new lift technology for aircraft. Please send email to
atxinter@xxxxxxxxx

Angle of attack control appears the most promising technology. A
variable attack wing is already in example exprimentally.

A simple method of doing the same appears to be the controled angle.
Meaning the flight control system causes the whole aircraft to change
angle and not just the wing. And conventional aircraft are already
simple tailed control surfaces.

A tailess wing has been perfected also. Still to improve the system is
a large and valuable task. I once ran into a real aircraft engineer.
They get prizes for removing even five pounds of weight from an
airliner.

So the actual task is hard. And the simple solution is a control
system for small aircraft with angle of attack indicators that are very
reliable. A new instrument panel indicator would allow the takeoff to
be perfected. And perfect human/machine interfacing is also a hard
thing.

What is displayed on the panel indicator, angle of attack?

A combination of angle and flight is the advanced conception of angle
of attack. A depth of stall indicator in reverse.

So take the wheel weight and then transform the angle of wind on the
wing.

And this is why it is not done in flight, absolute weight in relation
to capacity of lift is a hard thing to measure. A vertical vector to
measure weight will allow the panel meter to work inflight. A bad
design would use gps a good design would use the weight inferred from
the angle.

A set of indicators over the wing would allow the attack for the wing
which has a built in change to its angle. And the weight is then
inferred from the relation of one location to another. A descent as
the reduced power always effects the angle of attack meter in the same
fashion.

A fast speed decent would look normal flight, like, a slow speed decent
would look identical to the slow speed climb. The indicator places the
speed of the relative wind in relation to the absolute lift ability.

It is a large problem in high performance small aircraft. A stalled
takeoff angle will literrally cause the flight to never occur. And so
the normal takeoff is a long overextended takeoff.

So maybe think many angle indicators as a good approach. And design
the best angle indicator around.

A percentage of wing lift capacity as the vertical axis and quite nice
yaw indication for the horizontal axis. A yaw causes the lost total
lift capacity by changing the weigh and therefor the lift necessity of
the left or the right wing.

"Yawing to the left causes the right wing to have the indicator
decrease."

A flight control system is therefor the recommended idea.


Well that is the concept anyways.

.

Relevant Pages

  • Re: would an AOA indicator be helpful in a glider?
    ... Every book on airfoils from the venerable Abbot's "Theory of Wing ... airfoils coefficient of lift vs. angle of attack. ... their time flying near stall don't have them has always puzzled me. ...
    (rec.aviation.soaring)
  • Re: Flatboarding: the sailing style
    ... A symmetrical wing at zero angle of attack has zero lift. ... it will have no lift - it will be in a zero-G flight path. ...
    (rec.skiing.alpine)
  • Re: Wind on the Wing
    ... > attack is shown. ... > And in fact the heating of air by the underside of the ... > working wing is seen. ... > At some angle of attack a force of drag increases ...
    (sci.physics)
  • Re: McLarens "horns"
    ... incidence of the wing to the aircraft, which is somewhat akin to the hand out ... it demonstrates the stall angle of an airfoil (usually around 16 ... your "angle of attack" theory ...
    (rec.autos.sport.f1)
  • Re: Angle of attack - Relative wind
    ... I suspect you think the angle of attack is zero because ... the bottom of the airfoil is ... Supercritical wing, with almost flat uppersurface. ...
    (rec.aviation.student)
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