wonder if it pulls "g's" in proportion to its size, or greater?
I had to answer my own question: from what I see (and asking my aerospace engineer daughter who works for USAF for a general confirmation) and understood (without getting a headache) is the RC g's are, like any other airframe, are limited by its structure and power-to-weight ratios.
a thread attached where a modeler asked his fellow RC crowd about g's in their scale vs full size aircraft.
I conclude that, like for many model machines, humans could not survive the full-size "g" ride in many cases -- and structurally neither could some of our full-size machines:
Post#4
Here is my take on it from my rather rusty knowledge of aerodynamics.
In balanced (no sideslip) level flight in a banked turn, g force is 1/cos(angle of bank). (I'll call it g force but really g is an acceleration and is a multiple of acceleration due to gravity which is 9.81 m/s/s).
So at 60 degs, g = 2
75 deg, g = 3.86
80 deg, g = 5.76
85 deg, g = 11.47
Whether any particular aeroplane can fly at a particular angle of bank depends on how much lift it can produce. 10g basically means that the lift force is 10 times the weight of the aeroplane. The ability to generate this much lift depends on airspeed and coefficient of lift, which is closely related to angle of attack.
When you try to turn or pull up too hard what you are doing is increasing the angle of attack up to and beyond the stall angle and when the wing stalls lift is reduced. Maximum lift is achieved at maximum airspeed and at an angle of attack just below the stall, provided of course that the wings don't fall off .
As an example, my Jazz weighs about 90 oz. Motocalc says (very rough) that at maximum lift at full power is produced at an angle of attack of 7 deg and lift is 520oz. 520/90 = 5.8g.
Now I expect Motocalc's modelling of lift is a bit conservative but the figures are of the right order. In a dive, airspeed would be higher which would increase lift but I doubt if g force would get beyond about 7g.
What enables an F16 to pull 10+g and a Cessna 172 only about 2-3g (other than structural factors) is basically power. The Cessna wing stalls long before it is able to increase the lift force to 10 times weight. With our model aeroplanes, we can achieve very high power to weight ratios (Cessna 172 models that can climb vertically!) so perhaps we can get towards 10g with fast aircraft.
Post #8 Response to Post #4
your assessment is right-on! The amount of g-force an air vehicle can withstand is totally dependent upon it's structure, the amount of g-force an air vehicle can generate is dependent upon it's speed and aerodynamics (CL max), once an air vehicle exceeds it's CL max it will depart or destruct. At extremely high speed it is much more difficult to get to CL max than it is at low speed, SR-71 for example!
In the world of RC modeling, low Reynolds Number, you can get away with a lot that you could not do in a full scale with a human in the cockpit, although many WWII era spruce built biplanes can withstand +12g's, current day high performance fighters are limited to +9/-3 g's (structural limits), the g-onset rate is what causes pilot G-LOC, Loss-Of-Consciousness, pilots train to withstand sustained high g-loadings.
The way to test your model for structural integrity is to do it the same way full scale planes are done. In a static rig, support the fuselage and load the wings with evenlly distributed weights until they fail.