ONACA four digit"series airfoil NACA2412 The first digit: maximum camber in hundredths The second digit: the location of maximum camber along the chord from leading edge in tenth of the chord The last two digits: maximum thickness in hundredth of the chord NACA0012: symmetrical airfoil
NACA “four digit” series airfoil NACA2412: The first digit: maximum camber in hundredths; The second digit: the location of maximum camber along the chord from leading edge in tenth of the chord; The last two digits: maximum thickness in hundredth of the chord. NACA0012: symmetrical airfoil
4.3 Airfoil characteristics(experiment) Stall due t fow se paration CL max 0 lift slo =0
4.3 Airfoil characteristics(experiment)
◆ Special definitions C lift coefficient a angle of attack ao lift slope Lmax Maximum lift coefficient al-o zero-lift attack angle stall Consequence of the flow separation It is impossible for we to calculate c ma with inviscid flow approximation!!
Special definitions l c a0 l,max c L0 stall lift coefficient angle of attack lift slope Maximum lift coefficient zero-lift attack angle Consequence of the flow separation It is impossible for we to calculate with inviscid flow approximation!! l,max c
o Experiment results for NACA2412 NACA 2412 airfoil L=0 2. q1.(457) C12.0 1.6 C1ma×1.6 1.2 Lift coefficient 0.8 0.4 0 0 stall 16 -0.4 Eq.(4.64)--0.1 Moment 0.8 coefficient -0.2 0.3 oRe=3.l×10 回Re=8.9X10 0.4 8081624 a, degrees
Experiment results for NACA2412 0 L0 2.1 cl,max 1.6 0 stall 16
Source of drag 0.024 0.020 profile drag 0.016 口 0.012 Aerodynamic center 0.008 8a自 Drag coefficient 0.004 0 0 m ac -0.05 coefficient 0.1 ⊙Re=3.×10 0.15 日Re=89Xl0 12-8-40481216
Source of drag profile drag Aerodynamic center m ac c