Parasite Drag C Do for Wing and Tail surfaces (Ref. Raymer eq & eq.12.30)
Tail Geometry Horizontal Tail: Area = 2.2 Span = 3.0ft Chord = 0.73ft V h = 0.50 Vertical Tail - 25% added Area = 1.75 sq.ft Span = 1.63 ft Chord = 0.60 ft V v =
Drag vs Velocity Drag (lb)
Aerodynamic Properties Wetted area = 44.5 sq.ft. Span Efficiency Factor = 0.75 CL = 5.3 / rad CL e = /rad L/D max = 15.5 V loiter = 24 ft/s CL max = 1.55 CL cruise = 1.05 Xcg = (% MAC) Static Margin = 0.12 at Xcg = 0.35
Control Surface Sizing: Elevator Area Ratio = 0.45 Chord = 4 in. Rudder Area Ratio = 0.40 Single rudder of chord = 7.5 in. Ailerons Area Ratio = 0.10 Aileron chord = 3 in.
Testing Status and TBF: Model wing nearly complete Wind tunnel test with wake survey next week CMARC model of wing to predict derivatives Calculate Dihedral angle required Use wake data to predict propeller flowfield
Concerns Will we get the CLmax we are aiming for? Are the stability derivatives for ailerons correct? Will there be a variable stability system for it to matter? Will I be around for it to matter? Can we get some covering material to stick to the foam without looking like someone’s kid brother made it? Are the drag and power requirements correct to prevent being underpowered? STAY TUNED!