BBerson
Light Plane Philosopher
I need to load test one of my aft wing ribs. The design is similar to the Lazair with aft ribs that attach to the main D-cell structure and span to the trailing edge (no rear spar)
How do I calculate the load to put on a sample aft rib?
I checked my copy Basic Glider Criteria and found no help. The book said loads for ribs on single spar wings can be calculated using some NACA reports listed. But I found these NACA reports and nothing was relevant to testing ribs.
I know that the lift distribution is concentrated at the leading edge in high angle of attack, with much less air loads on the aft ribs. But I still want to test somehow. Also, if flaps are added this increases the rib load (but I won't need flaps) The ribs at the aileron bay would need to be stronger. How much?
Does anyone normally test these aft ribs? Or just copy other designs?
Thanks for any leads.
How do I calculate the load to put on a sample aft rib?
I checked my copy Basic Glider Criteria and found no help. The book said loads for ribs on single spar wings can be calculated using some NACA reports listed. But I found these NACA reports and nothing was relevant to testing ribs.
I know that the lift distribution is concentrated at the leading edge in high angle of attack, with much less air loads on the aft ribs. But I still want to test somehow. Also, if flaps are added this increases the rib load (but I won't need flaps) The ribs at the aileron bay would need to be stronger. How much?
Does anyone normally test these aft ribs? Or just copy other designs?
Thanks for any leads.
