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