Good Day all,
I have been spending a lot of time analyzing many different aerofoil profiles to optimize said profiles for a very specific flight regime. If there are any experts with good knowledge on foil analysis, Xfoil, laminar flow analysis, etc, I would love to have some discussions with you.
In essence I wish to optimize flight range, ie, kilometers flown, not endurance, under the following constraints:
AC AUW - 4.5kg, conventional form, ie, not flying wing, but with V tail, and ailerons and flaps.
Wing span max allowed 2.2meters, prefer 2meters
Max chord 310mm
Preferred cruise speed around 18m/s to 22m/s max
Practical Reynolds numbers from 380,000 to 450,000
Electric flight, prop in the nose.
Fuselage is low drag, whole A/C is fully composite molded.
I can use flaps for takeoff and land, but want MAX L/D ratio at around Re=400,000
I have analyzed a dozen wing profiles but would like some lateral insight....
I currently use a Clark-z foil, with max thickness of 13%, but want to improve on that.