All cases of AoA. Nothing to do with speed. Also Lift coefficient is subject to surface area. E.g. this would be what it looks like for delta wing
yet in no AoA situation this is completely different.
wtf are you saying
this is at a set speed of mach 2.5 showing drag at all conditions (AOA 0 degrees and above) is higher for grid fins than planar fins
it is not completely different in a no AOA situation, as you can see the graph extends to include the no AOA situation where even at mach 2.5 grid fins have 4 times the drag of planar fins and that discrepancy increases as mach number decreases
R-37M doesn’t use grid fins because it is a development from R-33, and R-33 was developed to be carried under MiG-31 fuselage on semi-recessed pylons. R-74M doesn’t use grid fins, same as R-73 because it’s designed with completely different layout scheme. If you are trying to prove a point please use arguments with a proof, not pure speculations.
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Bro you can just Integrate the grid cross section and compare with others, it is still higher, besides grid mean more surface area and creat more skin fractions, especially when you are turning.
The design meant to trade drag into turning capability, and now you said the drag is too high？
Huh？
Drag behaves differently at supersonic speeds.
And show that graphic with any amount of AOA, guess what happens?
It’s called a trade-off for a reason, and one that the rest of the world realized was not worth it
even at no AOA it is a lot higher, the paper I linked earlier stated over 4 times at 0 degrees AOA
It’s higher than the plane fins but in the game, the drag is much higher than irl, R77 can’t even reach 10 km lol
Right… We just straight up lying now I see
Does anyone have drag coeffecient to aoa comparison graph here for planar and grid?
wdym R77 can’t hit a maneuvering target at 10 km
Something seems fishy, they told in the paper that grid fins need to pull less for same aoa compared to planar fins, hence added drag should be less when turning compared to planar fins, but here the drag coeffecient across all aoa is equidistant, something is wrong…
no its not, that is fin AOA not missile AOA
I don’t think this comparision is that usefull, the planar fins taken is wierd, it’s not that long but a bit wide, whereas the grid fin taken is much bigger than the ones on r77.
Except that it can?
the comparison is between planar fins of a somewhat normal design and grid fins of the same area, which is the ideal options for a paper like this
Size matters too, different sizes can give different results, as mentioned in the paper
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yes but how can you compare two things if you change a bunch of variables
ideally you only change one variable which is why they changed the type of fin without changing the size
They haven’t kept the reference area the same though, meaning the grid fins’ lift and drag coefficient are not quite comparable. Also I reckon the grid fins are pretty rough models without having been modified for supersonic movement.
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