can anyone tell me what is standard (FAA) practice in accounting for fuselage effects when distributing load in a wing load test.Peery suggests the load is carried across the fuselage without any allowance for loss(ditto nacelles). The far 23 loads and other programs show the lift distribution from the a/c Center line also and make no mention of wing/fuse joint losses.
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wing load test-fuselage effects
- Thread starter ahjay
- Start date
Hi Ahjay:
The FAR 23.301 B) says : ... These loads must be distributed to conservatively or CLOSELY REPRESENT ACTUAL CONDITIONS ".
Actual condition may be a lift distribution considering the
fuselage influence ( with a lift loss ) see : "Aerodynamics,
Aeronautics and Flight Mechanics " , Barnes McCormick pag 144,
145,146.
Allways FAR's require conservative criteria to apply loads
( and good sense )
Cheers
Mohr
The FAR 23.301 B) says : ... These loads must be distributed to conservatively or CLOSELY REPRESENT ACTUAL CONDITIONS ".
Actual condition may be a lift distribution considering the
fuselage influence ( with a lift loss ) see : "Aerodynamics,
Aeronautics and Flight Mechanics " , Barnes McCormick pag 144,
145,146.
Allways FAR's require conservative criteria to apply loads
( and good sense )
Cheers
Mohr
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