Specs thus far: ( all theoretical at this point )

Wingspan: 14Ft
Wing Area (main wing- 2028 sq in) + ("t-canilizer winglet"- 250 sq in)= 2,278 sq in
Total TRF weight projections: 15-20lbs.
Batteries: 2x5S 25C 5,000-6,000 mah
Motor: 3,000 watt (likely a Neu motor
Propellor: Folding ??x?? << could use some imput here- propellor is going to be used in pusher style application
Fuselage: twin boom
Anything else im leaving out?

Iron eagle,

speed could possibly be an issue- I dont want to be flying mach 1 when taking these samples...afterall- one of the collection methods will be impact based. The other will partly rely on "ram" pressure created when the airplane is in forward motion. My moving to a delta wing, I would likely be flying at a much higher speed- am i correct? Also, I tihnk we are forgeting that a vast majority of testing will be done below 5K feet. Lets keep that in mind. The design has to be a compromise...

Thanks!
Brandon