What are the disadvantages of a tailless ultralight design with say 20 deg swept back wings with wing tip rudders, 20-60mph, max 25 hp?
I'm not an aerospace engineer, so I stand to be corrected:
The only 2 disadvantages I can think of are:
- Increased wing area/more weight/stronger spar
I understand the wing area would need to be larger as the "aerodynamic wing span" would be smaller than the physical wing span. I understand the wing only produces lift with the velocity component perpendicular to the leading edge ( which I understand would be V0*cos(radians(20)))
- Possible reduced or no side slip angle.
I understand you're not supposed to side slip a Velocity aircraft as the leeward wingtip vertical tail may stall ( rudders only move outward). I understand only the right rudder deflects outward when turning right ( the left rudder acting only as a vertical stabilizer, in this case) I'm attributing this to too thin of a vertical tail airfoil ( low stall angle ) with too high of an aspect ratio. ( I stand to be corrected on all the above). I understand Velocity reduced this problem by reducing the max angle of rudder deflection.
Are there any other disadvantages in terms of stability, cross wind landing, etc?
See pic below of the Mitchell Flying Wing: