n0012 Airfoil

NACA 0012 airfoil

n0012 Airfoil (x,y) Co-ordinates

0 0
0.0005839 0.0042603
0.0023342 0.0084289
0.0052468 0.0125011
0.0093149 0.0164706
0.0145291 0.02033
0.0208771 0.0240706
0.0283441 0.0276827
0.0369127 0.0311559
0.0465628 0.0344792
0.057272 0.0376414
0.0690152 0.040631
0.0817649 0.0434371
0.0954915 0.0460489
0.1101628 0.0484567
0.1257446 0.0506513
0.1422005 0.0526251
0.1594921 0.0543715
0.1775789 0.0558856
0.1964187 0.057164
0.2159676 0.0582048
0.2361799 0.0590081
0.2570083 0.0595755
0.2784042 0.0599102
0.3003177 0.0600172
0.3226976 0.0599028
0.3454915 0.0595747
0.3686463 0.0590419
0.3921079 0.0583145
0.4158215 0.0574033
0.4397317 0.05632
0.4637826 0.0550769
0.4879181 0.0536866
0.5120819 0.052162
0.5362174 0.0505161
0.5602683 0.0487619
0.5841786 0.0469124
0.6078921 0.0449802
0.6313537 0.0429778
0.6545085 0.0409174
0.6773025 0.0388109
0.6996823 0.03667
0.7215958 0.0345058
0.7429917 0.0323294
0.7638202 0.0301515
0.7840324 0.0279828
0.8035813 0.0258337
0.8224211 0.0237142
0.8405079 0.0216347
0.8577995 0.0196051
0.8742554 0.0176353
0.8898372 0.0157351
0.9045085 0.0139143
0.9182351 0.0121823
0.9309849 0.0105485
0.942728 0.0090217
0.9534372 0.0076108
0.9630873 0.0063238
0.9716559 0.0051685
0.9791229 0.0041519
0.9854709 0.0032804
0.990685 0.0025595
0.9947532 0.0019938
0.9976658 0.001587
0.9994161 0.0013419
1 0.00126
1 -0.00126
0.9994161 -0.0013419
0.9976658 -0.001587
0.9947532 -0.0019938
0.990685 -0.0025595
0.9854709 -0.0032804
0.9791229 -0.0041519
0.9716559 -0.0051685
0.9630873 -0.0063238
0.9534372 -0.0076108
0.942728 -0.0090217
0.9309849 -0.0105485
0.9182351 -0.0121823
0.9045085 -0.0139143
0.8898372 -0.0157351
0.8742554 -0.0176353
0.8577995 -0.0196051
0.8405079 -0.0216347
0.8224211 -0.0237142
0.8035813 -0.0258337
0.7840324 -0.0279828
0.7638202 -0.0301515
0.7429917 -0.0323294
0.7215958 -0.0345058
0.6996823 -0.03667
0.6773025 -0.0388109
0.6545085 -0.0409174
0.6313537 -0.0429778
0.6078921 -0.0449802
0.5841786 -0.0469124
0.5602683 -0.0487619
0.5362174 -0.0505161
0.5120819 -0.052162
0.4879181 -0.0536866
0.4637826 -0.0550769
0.4397317 -0.05632
0.4158215 -0.0574033
0.3921079 -0.0583145
0.3686463 -0.0590419
0.3454915 -0.0595747
0.3226976 -0.0599028
0.3003177 -0.0600172
0.2784042 -0.0599102
0.2570083 -0.0595755
0.2361799 -0.0590081
0.2159676 -0.0582048
0.1964187 -0.057164
0.1775789 -0.0558856
0.1594921 -0.0543715
0.1422005 -0.0526251
0.1257446 -0.0506513
0.1101628 -0.0484567
0.0954915 -0.0460489
0.0817649 -0.0434371
0.0690152 -0.040631
0.057272 -0.0376414
0.0465628 -0.0344792
0.0369127 -0.0311559
0.0283441 -0.0276827
0.0208771 -0.0240706
0.0145291 -0.02033
0.0093149 -0.0164706
0.0052468 -0.0125011
0.0023342 -0.0084289
0.0005839 -0.0042603
0 0

n0012 Airfoil CAD files

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