kingsbishop said:
Cant we just make the wings larger
Make them longer and the torque gets worse. An acrobat can barely support himself on outstretched arms.
No problem, you think. We'll just brace the two wings together with a spar and maybe even a spring. Yes, you can do that. It is called an airplane or hang glider. But if you want to make the thing human powered, you have a problem with the power to weight ratio. You need an athletic human and an ultralight craft.
https://en.wikipedia.org/wiki/Human-powered_aircraft
A propellor is vastly more efficient than a spring-loaded wing-flapping arrangement. I imagine that graphite composite beams with a Mylar skin are more effective than inflated rip-stop nylon fabric.
Edit: Looked up some power to weight ratios on
wikipedia.
For the engine alone we have figures like 2000 watts per kilogram (B29 engine) or up to 10,000 watts per kilogram (V22 Osprey). Or down as low as 30 watts per kilogram (Diesel engine in the
Emma Maersk container ship). Or up as high as 153,000 watts per kilogram (Space Shuttle main engine).
For
complete aircraft we have figures like 100-120 watts per kilogram (Spruce Goose, B17, B29), 300-350 watts per kilogram (Spitfire, P38, Bf 109, V22 Osprey). [Many high performance propellor driven craft in the 300's].
For an athletic bicyclist, we have 20 watts per kilogram as a 5 second maximum.
The
McReady Gossamer Condor weighed in at 31.5 kg (craft only, no pilot). I seem to recall 300 watts sustained for the pilot of the Gossamer Condor. That would put that particular craft plus pilot around 300 watts on a (completely guessed at) 100 kilograms gross vehicle weight for
3 watts per kilogram sustained.
[Chased the wikipedia reference to
https://www.trainingpeaks.com/blog/power-profiling/ and confirmed a rough factor of 5 difference between 5 second maximum and sustained power. That 3 watts per kilogram figure passes the sniff test]
Let us take the analysis one step further.
With 3 watts per kilogram of power, what sink rate can we tolerate in our aircraft so that we can make up for it with applied power? Or, equivalently, what climb rate would we have if the aircraft had zero drag?
The rate at which work must be done to achieve vertical velocity ##v## is given by ##P = mgv## where ##m## is the craft mass, ##g## is the acceleration of gravity and ##P## is the required power. We want to solve for ##v##:$$v=\frac{P}{mg} = \frac{P/m}{g}$$We know ##P/m = 3## watts per kilogram and we know that ##g = 9.8## m/s^2.
I make the result 0.3 meters per second -- a tolerable gliding sink rate of about one foot per second in a human powered craft.
This is a reasonable fit with what Wikipedia has to say:
https://en.wikipedia.org/wiki/Gliding_flight said:
A sink rate of approximately 1.0 m/s is the most that a practical hang glider or paraglider could have before it would limit the occasions that a climb was possible to only when there was strongly rising air. Gliders (sailplanes) have minimum sink rates of between 0.4 and 0.6 m/s depending on the
class.