The Wing-Tail Calculator might also be used to model the lift and vortex drag on a keel-rudder system or perhaps a double sail configuration. In these applications, however, one half of the wing-tail will model the actual device while the other half can model a surface image. (note: no explicit calculations are made in the software for this modification).
Wing-Tail accepts the following inputs for both the wing and tail: span, taper, sweep (forward and back), airfoil (just 4) and angle. The tail can be placed at arbitrary locations along the x-axis. The user must also enter the center of gravity location, profile drag at Cl=0, airplane weight & speed and whether or not to include ground effect in the calculations.
The Wing-Tail Calculation will compute lift, drag and moment coefficients, lift, drag and moment forces, location of the neutral point, mean aerodynamic chords, Cl_alpha, Cm_alpha, lift-drag-ratio and the minimum sink rate.
Wing-Tail can be used as an educational aide for learning about 3-d wings, induced drag, sweep, taper and longitudinal stability. It has 4 different airfoil for experimentation purposes. It is perfect for an introductory aerodynamics course, flight dynamics or aircraft conceptual design.
The introductory price of wing-tail is $29.00. The price at the end of the introductory period will be $45.00. Please purchase the software using the following url:
More information can be obtained from: