mcurcio1989
Well-Known Member
I am looking for some information on the procedure to perform static testing on a wing. The intent is to flip the wing upside down and use a test rig to attach the struts (flying wires actually), then load it up with sandbags. The questions as of now are:
Do we need to put it at a high angle of attack? In other words should the trailing edge be up 18° of so from the leading edge?
We know that wing loading is not linear and will vary based on the wing design, this is a hershey bar wing with a Riblet 30U-612 airfoil. I need some help with calculating how the load should be distributed. I know that you could probably write a thesis on this and spend days runnign calculations. I'm looking for good enough for government work ballpark figures.
Any other advice?
Thanks
Do we need to put it at a high angle of attack? In other words should the trailing edge be up 18° of so from the leading edge?
We know that wing loading is not linear and will vary based on the wing design, this is a hershey bar wing with a Riblet 30U-612 airfoil. I need some help with calculating how the load should be distributed. I know that you could probably write a thesis on this and spend days runnign calculations. I'm looking for good enough for government work ballpark figures.
Any other advice?
Thanks
