Canard-Wing Configuration: Canard configuration refers to airframe configuration

Question

Canard-Wing Configuration: Canard configuration refers to airframe configuration where horizontal tail is located in front of the main wing rather than being aft of the wing. Due to its front configuration, the canard surface is subjected to upwash due to main wing rather than downwash experienced by aft tail. Your task is to develop an expression for the pitching moment coefficient about the center of gravity for canard-wing combination. Clearly state all assumptions that you may make to simplify the problem. For example, you may want to neglect the drag contribution and assume angle of attack to be small. Furthermore, find an expression for neutral point for this airplane.

Explanation / Answer

the equation neutral point is

hn = h0 + hs V s (as / aw) (1 - (de / da ))

where

The typical values for h 0 , h s and de / da are more than adequate in most cases. All that is needed are the stabiliser-volume and lift-curve values.

h n neutral-point h 0 aerodynamic center of the wing, typically 0.25 h s stabilizer efficiency typcially 0.6 (0.9 for a T-tail) V s stabiliser volume coefficient as lift curve slope of stabiliser aw lift curve slope of wing de / da change in stabiliser downwash angle versus change in wing angle-of-attack, typically 0.5 to 0.33

Related Questions

Navigate

• Browse (All)
• Browse C
• Subjects

---

---

Integrity-first tutoring: explanations and feedback only — we do not complete graded work. Learn more.