Em que ângulo de ataque (ângulo da inclinação lateral) uma barbatana vertical simétrica mais um leme desviado teriam um coeficiente de sustentação de exatamente zero?

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Em que ângulo de ataque (ângulo da inclinação lateral) uma barbatana vertical simétrica mais um leme desviado teriam um coeficiente de sustentação de exatamente zero?

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For rudder deflection angles of 5, 10, 20, 30, and 45 degrees, at what (negative) angle-of-attack does a fin-rudder combination (including dorsal fin if present) have a lift coefficient of exactly zero?

For the purpose of this question, define angle-of-attack in relation to the chord line of the fin alone, not including the deflected rudder. If we ignore things like spiral slipstream, deflection of airflow around cabin, etc, it would be the same as the sideslip angle.

Loosely speaking, at this angle-of-attack we could say the force from the deflected rudder is being exactly cancelled by the force from the fin, though in reality each influences the airflow around the other and the fin-rudder combination acts as a single unit.

To allow for a definitive answer, I'll specify to use the fin (including dorsal fin) and rudder from current -production Cessna 172 S, but feel to post an answer addressing the fin and rudder from any other aircraft.

Note that an aircraft could never sustain a sideslip angle that caused the fin plus deflected rudder to have a lift coefficient of zero, unless some other yaw torque due to something like asymmetric thrust or extreme adverse yaw from deflected ailerons was acting to maintain the slip angle.

As aproximações são boas - obviamente uma resposta exata envolveria um projeto complicado de modelagem por computador ou experimentos reais em túneis de vento. Minha esperança é que as informações existentes relacionadas às curvas de sustentação de perfis aerodinâmicos simétricos com abas implantadas possam ser adaptadas para dar uma aproximação de uma resposta a esta pergunta.

aerodinâmica estabilidade mecânica de vôo leme derrapagem

por folheto silencioso 02.08.2019 / 20:04

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Tags aerodinâmica estabilidade mecânica de vôo leme derrapagem

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score 1 · Answer 1

Here are two links to Tom Speer's homepage. They show the performance of a couple of flapped airfoils. They aren't symmetrical, but it doesn't matter for what you are doing. What you want to look at is the change in the AoA between adjacent flap deflections.

For instance, it the first link, the there is a series for -3 degrees flap and one for 5 degrees flap. Holding the coefficient of lift constant, you'll see about a 4 degree difference in AoA. Thus deflecting a smallish 20% flap is about the same as rotating the whole foil by half as much.

http://www.tspeer.com/NACA23012/N23012wflap.htm
http://www.tspeer.com/NACA23012/N23012wflap.htm

For a 50% flap, it can be as much as 80% effective. See also Tom's analyses of wingsail performance with various sized flaps at the same site. These are symmetric foils, but you have to do some extrapolation to run the lift down to zero.

Tom worked for Boeing, and has worked on numerous high performance projects including the America's cup wingsails and landyacht projects.

score 0 · Answer 2

If you want an approximate answer, it is any time a steady heading sideslip is performed (rudder vs. resulting sideslip). It's approximate because the fuselage and ailerons also contribute to the yawing. But if the fuselage is only mildly destabilizing, the answer should be in the ball park.