Hey gents,
Another noob question here. I've been looking at drag polars for a lot of different airfoils and it seems that many decently thin ones that operate in the range of 100,000 Re to 150,000 Re or so seem to have max L/D ratios of around 50 and above. Granted, this is just the airfoil - and also doesn't factor in induced drag - that I'm aware of. However, unless we're talking about high performance gliders, it seems to be rare that any airframe has that sort of max L/D. Props, fuselages, tails, and a plethora of other drag-creating odds and ends attached to the airplane seem to really bring that number down significantly from the max L/D of the wing itself. To compound the drag issue, it seems that little model airplanes suffer from higher drag coefficients because of their low reynolds numbers. However, it seems like one possible way to help this issue would be to use a pure flying wing like a zagi / zephyr. So I've got two questions:
1.) What, at least in your personal opinion, would you consider a poor, medium, and good L/D ratio for a powered model airplane?
2.) Is there enough benefit from a
pure flying wing like a zagi, or a plank to outweigh the stability issues they pose?
I've used spreadsheets to tinker with different variables like aspect ratio, span efficiency, zero lift drag coefficient, etc to try to get rough ideas of L/D for my models, but I'd really like to know what you guys consider to be the good, the bad and the ugly.
Regards,
-DE