Device can measures total drag force and lift of wing for given AoA and airflow speed. Wing both wingtips are far away from side walls. Airflow speed is constant all the time:50m/s
TOTAL DRAG=MEASURED DRAG
TOTAL DRAG =ZERO LIFT DRAG + INDUCED DRAG
TOTAL DRAG=PROFILE DRAG +INDUCED DRAG
profile drag=skin friction drag + pressure drag
•First I put wing at zero-lift angle: it show 500N drag force
•Then I put wing at 15° AoA:it show 700N drag force
So for 15° AoA and 50m/s:
"Profile drag"(Skin friction + pressure drag) is 500N and induced drag is 200N(700-500).
Is this correct calculation?