- #1
Jurgen M
v=50m/s
βPg= -981Pa
βππ =490Pa
c=1m
π = 1,225 kg m3
πΉ3 = β« βπ3 β 1 β ππ₯ π 2 0 = βππ β« 2βππ π π₯ππ₯ π 2 0 = 2βππ π β ( π₯ 2 2 ) cβ2 | 0 = 2βππ π β π 2 4 β 2 = βππ β π 4 = 490,5 β 1 4 = 122,625 N
Lift per unit of span = (F1) + (F2) +F3 + F4= 490.5+245.25+122,25+122,625=981N
Pressure push at all surfaces on airfoil,just push with less force on upper surface then lower surface, so F1 and F2 must has opposite direction than F3 ,F4.. so why they sum all forces with absolute values like pressure at upper surface pulling...?? pressure can not pull,only push
Dont understand final lift math and force orientation..
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