The r Derivatives (Cyr, Clr, СПг)

Подпись: or The r Derivatives (Cyr, Clr, СПг)

When an airplane has a rate of yaw r superimposed on the foward motion u0, its ve­locity field is altered significantly. This is illustrated for the wing and vertical tail in Fig. 5.16. The situation on the wing is clearly very complicated when it has much sweepback. The main feature however, is that the velocity of the chord line normal to itself is increased by the yawing on the left-hand side, and decreased on the right side. The aerodynamic forces at each section (lift, drag, moment) are therefore in­creased on the left-hand side, and decreased on the right-hand side. As in the case of the rolling wing, the unsymmetrical lift distribution leads to an unsymmetrical trail­ing vortex sheet, and hence a sidewash at the tail. The incremental tail angle of attack is then

THE DERIVATIVE Cyr

The r Derivatives (Cyr, Clr, СПг) Подпись: - /0 IF da a”rY 2T + IF

The only contribution to СУг that is normally important is that of the tail. From the an­gle of attack change we find the incremental Cy to be

thus

Подпись: (Cyr)tail aF cПодпись: da dr The r Derivatives (Cyr, Clr, СПг)(5.8,2)

THE DERIVATIVE Clr

This is another important cross derivative; the rolling moment due to yawing. The in­crease in lift on the left wing, and the decrease on the right wing combine to produce a positive rolling moment proportional to the original lift coefficient CL. Hence this derivative is largest at low speed. Aspect ratio, taper ratio, and sweepback are all im­portant parameters.

When the vertical tail is large, its contribution may be significant. A formula for it can be derived in the same way as for the previous tail contributions, with the result

Sf? Zf I Ip da

«y.„ = «,T17(2T + 1f) <5ад

THE DERIVATIVE C„r

C„r is the damping-in-yaw derivative, and is always negative. The body adds a negli­gible amount to Cnr except when it is very large. The important contributions are those of the wing and tail. The increases in both the profile and induced drag on the left wing and the decreases on the right wing give a negative yawing moment and hence a resistance to the motion. The magnitude of the effect depends on the aspect ratio, taper ratio, and sweepback. For extremely large sweepback, of the order of 60°, the yawing moment associated with the induced drag may be positive; that is, pro­duce a reduction in the damping.

The side force on the tail also provides a negative yawing moment. The calcula­tion is similar to that for the preceding tail contributions, with the result

( If da

(CJtail = ~aFVv (2- + —) (5.8,4)

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