# Airforil for Tailless Aircraft

## Airforil for Tailless Aircraft

• Submitted By: konohamaru
• Date Submitted: 11/03/2008 7:45 AM
• Category: Science
• Words: 2573
• Page: 11
• Views: 1

Airfoils for Tailless Airplanes:
Design and Selection

Airplane Types and Moment Coefficient

Besides lift and drag coefficients, the moment coefficient cm is of importance for the behaviour of an airplane - it has a big impact on the longitudinal stability. While a conventional airplane can compensate the moment of the wing with its horizontal tail, a tailless plane obviously can't.
It is possible to divide tailless airplanes in three groups, depending on how they achieve longitudinal stability. The requirements for the moment coefficient of the airfoil is a direct result of the stabilizing mechanism.
• wing without sweep (plank)
Longitudinal stability is created solely by the airfoil. A plank requires an airfoil with a positive moment coefficient.
• swept wing
It is possible to use any airfoil, because longitudinal stability can always be achieved by selecting a suitable combination of sweep and twist. For best allround performance, airfoils with low moment coefficients (around zero) are better suited although. They need smaller amounts of twist, which results in a broader speed range without paying too much penalties off the design point.
• wing with a low position of the center of gravity (parafoil)
The moment coefficient is less important and it is possible to use traditional airfoils with negative moment coefficients. The position of the c.g. can be chosen to guarantee stability, but usually airfoils with medium moment coefficients are chosen to achieve higher penetration speeds and a wider speed range.
[pic][pic][pic]
Classes of tailless airplanes and their typical moment coefficients.
Remark:
To achieve static longitudinal stability, the center of gravity (c.g.) must be located in front of the neutral point, which makes the momentum derivative dCm/dAlfa (rel. c.g.) negative. Placing the c.g. in the neutral point results in dCm/dAlfa = 0, making the plane indifferent, i.e. it will not stabilize itself after a...