XFOIL Version 6.96 Calculated polar for: NACA 0012 AIRFOILS 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -1.2258 0.10236 0.09929 -0.0012 1.0000 0.0135 -18.250 -1.2456 0.09505 0.09187 -0.0049 1.0000 0.0136 -18.000 -1.2659 0.08782 0.08451 -0.0086 1.0000 0.0136 -17.750 -1.2852 0.08088 0.07744 -0.0121 1.0000 0.0136 -17.500 -1.3031 0.07429 0.07074 -0.0154 1.0000 0.0137 -17.250 -1.3193 0.06814 0.06446 -0.0185 1.0000 0.0137 -17.000 -1.3322 0.06256 0.05874 -0.0213 1.0000 0.0137 -16.750 -1.3427 0.05745 0.05351 -0.0238 1.0000 0.0138 -16.500 -1.3519 0.05263 0.04856 -0.0261 1.0000 0.0139 -16.250 -1.3687 0.04704 0.04283 -0.0285 1.0000 0.0140 -16.000 -1.3806 0.04234 0.03800 -0.0303 1.0000 0.0142 -15.750 -1.3868 0.03865 0.03420 -0.0313 1.0000 0.0144 -15.500 -1.3879 0.03577 0.03122 -0.0317 1.0000 0.0146 -15.250 -1.3854 0.03348 0.02885 -0.0317 1.0000 0.0148 -15.000 -1.3802 0.03160 0.02690 -0.0313 1.0000 0.0151 -14.750 -1.3739 0.02997 0.02518 -0.0305 1.0000 0.0153 -14.500 -1.3669 0.02849 0.02363 -0.0295 1.0000 0.0156 -14.250 -1.3590 0.02718 0.02223 -0.0283 1.0000 0.0159 -14.000 -1.3502 0.02602 0.02099 -0.0268 1.0000 0.0162 -13.750 -1.3399 0.02502 0.01991 -0.0252 1.0000 0.0164 -13.500 -1.3281 0.02416 0.01896 -0.0236 1.0000 0.0167 -13.250 -1.3149 0.02343 0.01816 -0.0219 1.0000 0.0169 -13.000 -1.3132 0.02207 0.01670 -0.0187 1.0000 0.0174 -12.750 -1.3004 0.02117 0.01576 -0.0169 1.0000 0.0179 -12.500 -1.2834 0.02049 0.01504 -0.0156 1.0000 0.0183 -12.250 -1.2649 0.01988 0.01438 -0.0144 1.0000 0.0188 -12.000 -1.2455 0.01931 0.01376 -0.0134 1.0000 0.0194 -11.750 -1.2250 0.01881 0.01321 -0.0124 1.0000 0.0199 -11.500 -1.2032 0.01839 0.01274 -0.0116 1.0000 0.0203 -11.250 -1.1872 0.01745 0.01175 -0.0101 1.0000 0.0213 -11.000 -1.1666 0.01690 0.01118 -0.0091 1.0000 0.0220 -10.750 -1.1449 0.01645 0.01069 -0.0082 1.0000 0.0228 -10.500 -1.1228 0.01602 0.01023 -0.0074 1.0000 0.0236 -10.250 -1.1000 0.01566 0.00982 -0.0066 1.0000 0.0242 -10.000 -1.0807 0.01499 0.00912 -0.0053 1.0000 0.0255 -9.750 -1.0591 0.01456 0.00868 -0.0043 1.0000 0.0266 -9.500 -1.0368 0.01423 0.00833 -0.0034 1.0000 0.0278 -9.250 -1.0143 0.01395 0.00801 -0.0024 1.0000 0.0288 -9.000 -0.9948 0.01341 0.00747 -0.0010 1.0000 0.0306 -8.750 -0.9735 0.01307 0.00712 0.0002 1.0000 0.0322 -8.500 -0.9517 0.01279 0.00682 0.0014 1.0000 0.0337 -8.250 -0.9313 0.01240 0.00642 0.0027 1.0000 0.0358 -8.000 -0.9104 0.01209 0.00612 0.0040 1.0000 0.0382 -7.750 -0.8888 0.01187 0.00587 0.0052 1.0000 0.0401 -7.500 -0.8687 0.01149 0.00552 0.0067 1.0000 0.0435 -7.250 -0.8475 0.01124 0.00527 0.0080 1.0000 0.0464 -7.000 -0.8268 0.01095 0.00500 0.0093 1.0000 0.0505 -6.750 -0.7975 0.01069 0.00475 0.0088 0.9992 0.0550 -6.500 -0.7634 0.01034 0.00446 0.0073 0.9975 0.0624 -6.250 -0.7289 0.01003 0.00419 0.0058 0.9959 0.0709 -6.000 -0.6939 0.00973 0.00395 0.0041 0.9944 0.0815 -5.750 -0.6601 0.00942 0.00371 0.0026 0.9924 0.0940 -5.500 -0.6268 0.00911 0.00348 0.0014 0.9897 0.1090 -5.000 -0.5571 0.00847 0.00304 -0.0019 0.9853 0.1490 -4.750 -0.5213 0.00816 0.00284 -0.0038 0.9836 0.1728 -4.500 -0.4903 0.00786 0.00266 -0.0045 0.9789 0.1984 -4.250 -0.4588 0.00756 0.00248 -0.0053 0.9738 0.2257 -4.000 -0.4276 0.00728 0.00232 -0.0061 0.9687 0.2535 -3.750 -0.4004 0.00705 0.00217 -0.0058 0.9599 0.2804 -3.500 -0.3730 0.00681 0.00204 -0.0057 0.9511 0.3089 -3.250 -0.3462 0.00659 0.00191 -0.0053 0.9409 0.3366 -3.000 -0.3201 0.00640 0.00180 -0.0048 0.9284 0.3637 -2.750 -0.2938 0.00623 0.00170 -0.0043 0.9152 0.3920 -2.500 -0.2675 0.00606 0.00160 -0.0038 0.9007 0.4195 -2.250 -0.2410 0.00593 0.00151 -0.0034 0.8848 0.4469 -2.000 -0.2144 0.00581 0.00144 -0.0030 0.8675 0.4744 -1.750 -0.1878 0.00570 0.00137 -0.0025 0.8486 0.5014 -1.500 -0.1611 0.00562 0.00131 -0.0021 0.8283 0.5286 -1.250 -0.1343 0.00556 0.00126 -0.0018 0.8072 0.5556 -1.000 -0.1075 0.00549 0.00122 -0.0014 0.7848 0.5826 -0.750 -0.0806 0.00546 0.00118 -0.0010 0.7610 0.6087 -0.500 -0.0538 0.00542 0.00116 -0.0007 0.7373 0.6352 -0.250 -0.0268 0.00541 0.00115 -0.0004 0.7123 0.6609 0.000 0.0000 0.00540 0.00114 0.0000 0.6872 0.6873 0.250 0.0269 0.00541 0.00115 0.0003 0.6611 0.7123 0.500 0.0538 0.00542 0.00116 0.0007 0.6353 0.7372 0.750 0.0806 0.00546 0.00118 0.0010 0.6088 0.7609 1.000 0.1075 0.00549 0.00122 0.0014 0.5826 0.7847 1.250 0.1344 0.00555 0.00126 0.0018 0.5560 0.8071 1.500 0.1611 0.00562 0.00131 0.0021 0.5281 0.8282 1.750 0.1878 0.00570 0.00137 0.0025 0.5018 0.8484 2.000 0.2144 0.00581 0.00144 0.0030 0.4743 0.8675 2.250 0.2410 0.00593 0.00151 0.0034 0.4468 0.8848 2.500 0.2675 0.00606 0.00160 0.0038 0.4196 0.9007 2.750 0.2938 0.00623 0.00170 0.0043 0.3917 0.9152 3.000 0.3201 0.00640 0.00180 0.0048 0.3637 0.9285 3.250 0.3462 0.00659 0.00191 0.0053 0.3366 0.9409 3.500 0.3730 0.00681 0.00204 0.0057 0.3090 0.9511 3.750 0.4004 0.00705 0.00218 0.0058 0.2803 0.9599 4.000 0.4276 0.00728 0.00232 0.0061 0.2536 0.9688 4.250 0.4588 0.00756 0.00248 0.0053 0.2255 0.9738 4.500 0.4903 0.00786 0.00265 0.0045 0.1986 0.9789 4.750 0.5213 0.00816 0.00284 0.0038 0.1728 0.9836 5.000 0.5572 0.00847 0.00304 0.0019 0.1488 0.9853 5.500 0.6268 0.00911 0.00348 -0.0014 0.1090 0.9897 5.750 0.6601 0.00942 0.00371 -0.0027 0.0939 0.9924 6.000 0.6940 0.00972 0.00395 -0.0041 0.0816 0.9944 6.250 0.7290 0.01003 0.00419 -0.0058 0.0709 0.9959 6.500 0.7635 0.01034 0.00446 -0.0074 0.0624 0.9976 6.750 0.7976 0.01069 0.00475 -0.0089 0.0550 0.9992 7.000 0.8267 0.01095 0.00499 -0.0093 0.0505 1.0000 7.250 0.8474 0.01124 0.00527 -0.0080 0.0464 1.0000 7.500 0.8686 0.01149 0.00552 -0.0067 0.0435 1.0000 7.750 0.8887 0.01186 0.00587 -0.0052 0.0401 1.0000 8.000 0.9103 0.01208 0.00612 -0.0040 0.0382 1.0000 8.250 0.9312 0.01240 0.00642 -0.0027 0.0359 1.0000 8.500 0.9516 0.01279 0.00682 -0.0013 0.0337 1.0000 8.750 0.9734 0.01307 0.00712 -0.0002 0.0322 1.0000 9.000 0.9948 0.01341 0.00747 0.0010 0.0306 1.0000 9.250 1.0143 0.01395 0.00801 0.0024 0.0288 1.0000 9.500 1.0368 0.01423 0.00832 0.0034 0.0278 1.0000 9.750 1.0591 0.01456 0.00868 0.0043 0.0266 1.0000 10.000 1.0808 0.01499 0.00912 0.0053 0.0255 1.0000 10.250 1.1001 0.01566 0.00982 0.0066 0.0242 1.0000 10.500 1.1229 0.01602 0.01023 0.0074 0.0236 1.0000 10.750 1.1450 0.01645 0.01069 0.0082 0.0228 1.0000 11.000 1.1668 0.01690 0.01118 0.0091 0.0220 1.0000 11.250 1.1874 0.01745 0.01175 0.0100 0.0213 1.0000 11.500 1.2033 0.01840 0.01274 0.0116 0.0203 1.0000 11.750 1.2251 0.01881 0.01321 0.0124 0.0199 1.0000 12.000 1.2457 0.01931 0.01376 0.0133 0.0194 1.0000 12.250 1.2651 0.01988 0.01438 0.0144 0.0188 1.0000 12.500 1.2837 0.02049 0.01504 0.0155 0.0183 1.0000 12.750 1.3008 0.02117 0.01576 0.0168 0.0179 1.0000 13.000 1.3137 0.02207 0.01670 0.0186 0.0174 1.0000 13.250 1.3157 0.02342 0.01815 0.0218 0.0169 1.0000 13.500 1.3290 0.02415 0.01895 0.0235 0.0167 1.0000 13.750 1.3406 0.02502 0.01991 0.0251 0.0164 1.0000 14.000 1.3509 0.02602 0.02099 0.0267 0.0162 1.0000 14.250 1.3600 0.02717 0.02222 0.0281 0.0159 1.0000 14.500 1.3679 0.02848 0.02361 0.0294 0.0156 1.0000 14.750 1.3750 0.02995 0.02516 0.0304 0.0153 1.0000 15.000 1.3814 0.03158 0.02687 0.0311 0.0151 1.0000 15.250 1.3864 0.03348 0.02885 0.0315 0.0148 1.0000 15.500 1.3892 0.03575 0.03121 0.0315 0.0146 1.0000 15.750 1.3881 0.03863 0.03418 0.0311 0.0144 1.0000 16.000 1.3818 0.04235 0.03800 0.0300 0.0142 1.0000 16.250 1.3702 0.04702 0.04280 0.0282 0.0140 1.0000 16.500 1.3536 0.05261 0.04854 0.0258 0.0139 1.0000 16.750 1.3451 0.05734 0.05340 0.0235 0.0138 1.0000 17.000 1.3352 0.06237 0.05856 0.0211 0.0137 1.0000 17.250 1.3218 0.06802 0.06434 0.0182 0.0137 1.0000 17.500 1.3059 0.07416 0.07060 0.0152 0.0136 1.0000 17.750 1.2880 0.08075 0.07731 0.0118 0.0136 1.0000 18.000 1.2685 0.08773 0.08442 0.0083 0.0136 1.0000 18.250 1.2485 0.09493 0.09174 0.0046 0.0136 1.0000 18.500 1.2284 0.10229 0.09922 0.0008 0.0135 1.0000