I'm looking for some aircraft data, but can't find it.

What I'd need:

-common, minimum and maximum values for acceleration and deceleration of aircraft during landing approach due to winds, and for example putting the throttle suddenly at zero or max.

-the same for altitude changes, hence common, min and max ascent/descent rate due to changing throttle, gusts, steering errors... So not the (3°) descend slope, but possible disturbance rates on this.

Any input is welcome. I'd prefer to know for which (type of) craft they are valid and have a source, but if you're just sharing your knowledge/experience without having a source, it's also a good start. I'm looking into airliners, jet aircraft and gliders. Other craft are also welcome, maybe I could extrapolate.

The reason behind this is that I want to apply a realistic range of disturbances on a landing approach, but I'd like to know how fast I'd need to transition between "reference" and "reference + disturbance" for velocity and altitude.

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Have you tried asking a flight instructor?

I've spoken to some pilots, but they couldn't immediately tell me in what range those values were. But I'm still looking it up, I'll find something eventually .

I was thinking that for putting the throttle completely at zero, I could take just pure drag deceleration, maybe with rounding the "edges" off.
For vertical gusts, I could assume that after a transition period the distubance has the same velocity as the gusts, especially for small craft?

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On my Piper Cherokee, when I pulled back the throttle, the plane maintains the same trimmed airspeed but begins to descend. For example, if I'm trimmed to fly at 100 MPH in level flight, chopping the throttle will cause the plane to descend at 100 MPH airspeed. It'll only slow down if I try to maintain the same altitude while chopping power.

It might be different for high performance or jet powered aircraft. All of my flying experience is with private planes.

Try asking on this forum
http://www.aviationforum.org/forums/...?s=&forumid=25

you could also ask some of the flight simulator people, if you can find them (I don't mean MicroBarf - I mean the training simulators)..

Or - this is a long shot - take a look at airresearch.com. I don't think he keeps that kiind of data (it's mostly about aviation accidents), but I know the guy behind the curtain, and he might be able to at least point you in the right direction.

Does anyone know some drag coefficient values in vertical direction? Cd is for the in flight direction, but I'd like to know some values in perpendicular to flight direction . (no, not Cl, but the drag of the planform of the craft)

edit: 50% flat plate + 50% tube should be a good approximation.

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