XFOIL Version 6.96 Calculated polar for: NACA 63-212 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.9225 0.08473 0.08249 -0.0238 1.0000 0.0078 -15.250 -0.9530 0.07394 0.07152 -0.0309 1.0000 0.0078 -15.000 -0.9767 0.06556 0.06297 -0.0365 1.0000 0.0078 -14.750 -0.9974 0.05848 0.05573 -0.0410 1.0000 0.0078 -14.500 -1.0109 0.05306 0.05016 -0.0442 1.0000 0.0078 -14.250 -1.0251 0.04796 0.04490 -0.0468 1.0000 0.0078 -14.000 -1.0319 0.04415 0.04095 -0.0485 1.0000 0.0079 -13.750 -1.0372 0.04078 0.03744 -0.0497 1.0000 0.0079 -13.500 -1.0386 0.03805 0.03459 -0.0503 1.0000 0.0080 -13.250 -1.0415 0.03533 0.03172 -0.0505 1.0000 0.0081 -13.000 -1.0404 0.03320 0.02947 -0.0503 1.0000 0.0082 -12.750 -1.0410 0.03102 0.02716 -0.0497 1.0000 0.0081 -12.500 -1.0377 0.02938 0.02540 -0.0487 1.0000 0.0082 -12.250 -1.0336 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0.00643 0.00128 -0.0417 0.4738 0.6733 2.750 0.4866 0.00665 0.00139 -0.0417 0.4348 0.6806 3.000 0.5130 0.00700 0.00154 -0.0416 0.3818 0.6887 3.250 0.5387 0.00745 0.00175 -0.0414 0.3186 0.6962 3.500 0.5646 0.00786 0.00198 -0.0413 0.2664 0.7041 3.750 0.5902 0.00832 0.00224 -0.0412 0.2126 0.7114 4.000 0.6152 0.00886 0.00254 -0.0409 0.1531 0.7196 4.250 0.6403 0.00936 0.00284 -0.0407 0.1039 0.7269 4.500 0.6662 0.00975 0.00311 -0.0406 0.0741 0.7351 4.750 0.6923 0.01008 0.00337 -0.0404 0.0538 0.7427 5.000 0.7186 0.01037 0.00362 -0.0403 0.0409 0.7511 5.250 0.7452 0.01062 0.00386 -0.0402 0.0343 0.7589 5.500 0.7718 0.01085 0.00411 -0.0401 0.0300 0.7678 5.750 0.7981 0.01111 0.00437 -0.0399 0.0263 0.7764 6.250 0.8506 0.01159 0.00492 -0.0396 0.0214 0.7944 6.500 0.8764 0.01188 0.00523 -0.0394 0.0191 0.8033 6.750 0.9022 0.01213 0.00553 -0.0392 0.0177 0.8128 7.000 0.9275 0.01243 0.00585 -0.0389 0.0162 0.8218 7.250 0.9524 0.01278 0.00623 -0.0385 0.0149 0.8312 7.500 0.9774 0.01307 0.00659 -0.0382 0.0143 0.8411 7.750 1.0020 0.01338 0.00696 -0.0377 0.0137 0.8516 8.250 1.0495 0.01408 0.00775 -0.0367 0.0124 0.8756 8.500 1.0720 0.01447 0.00820 -0.0359 0.0120 0.8890 8.750 1.0928 0.01496 0.00878 -0.0349 0.0114 0.9051 9.000 1.1134 0.01532 0.00923 -0.0337 0.0113 0.9250 9.250 1.1330 0.01567 0.00968 -0.0324 0.0111 0.9600 9.500 1.1577 0.01615 0.01022 -0.0323 0.0109 1.0000 9.750 1.1797 0.01666 0.01078 -0.0317 0.0107 1.0000 10.000 1.2008 0.01722 0.01139 -0.0309 0.0105 1.0000 10.250 1.2213 0.01779 0.01200 -0.0301 0.0103 1.0000 10.500 1.2410 0.01838 0.01264 -0.0292 0.0101 1.0000 10.750 1.2600 0.01898 0.01328 -0.0282 0.0099 1.0000 11.000 1.2785 0.01957 0.01391 -0.0272 0.0097 1.0000 11.250 1.2946 0.02020 0.01460 -0.0258 0.0095 1.0000 11.500 1.3074 0.02088 0.01533 -0.0238 0.0093 1.0000 11.750 1.3182 0.02167 0.01617 -0.0218 0.0092 1.0000 12.000 1.3283 0.02255 0.01711 -0.0198 0.0090 1.0000 12.250 1.3364 0.02362 0.01825 -0.0178 0.0089 1.0000 12.500 1.3434 0.02482 0.01954 -0.0160 0.0087 1.0000 12.750 1.3465 0.02641 0.02122 -0.0141 0.0085 1.0000 13.000 1.3563 0.02757 0.02245 -0.0129 0.0085 1.0000 13.250 1.3642 0.02894 0.02392 -0.0117 0.0085 1.0000 13.500 1.3725 0.03033 0.02539 -0.0107 0.0084 1.0000 13.750 1.3803 0.03182 0.02697 -0.0098 0.0083 1.0000 14.000 1.3868 0.03349 0.02873 -0.0091 0.0082 1.0000 14.250 1.3947 0.03509 0.03041 -0.0085 0.0080 1.0000 14.500 1.3974 0.03724 0.03267 -0.0079 0.0080 1.0000 14.750 1.4040 0.03908 0.03460 -0.0076 0.0079 1.0000 15.000 1.4064 0.04144 0.03705 -0.0074 0.0078 1.0000 15.250 1.4082 0.04394 0.03965 -0.0074 0.0077 1.0000 15.500 1.4098 0.04655 0.04236 -0.0076 0.0076 1.0000 15.750 1.4088 0.04957 0.04549 -0.0080 0.0075 1.0000 16.000 1.4074 0.05274 0.04878 -0.0087 0.0075 1.0000 16.250 1.4055 0.05614 0.05229 -0.0095 0.0074 1.0000 16.500 1.3999 0.06020 0.05647 -0.0108 0.0074 1.0000 16.750 1.3978 0.06394 0.06031 -0.0122 0.0073 1.0000 17.000 1.3910 0.06854 0.06504 -0.0141 0.0072 1.0000 17.250 1.3812 0.07384 0.07047 -0.0164 0.0072 1.0000 17.500 1.3718 0.07929 0.07604 -0.0191 0.0072 1.0000 17.750 1.3616 0.08511 0.08199 -0.0221 0.0071 1.0000 18.000 1.3488 0.09166 0.08867 -0.0256 0.0071 1.0000 18.250 1.3339 0.09885 0.09600 -0.0296 0.0070 1.0000 18.500 1.3162 0.10691 0.10420 -0.0343 0.0070 1.0000 18.750 1.2937 0.11630 0.11375 -0.0399 0.0070 1.0000 19.000 1.2709 0.12603 0.12363 -0.0458 0.0070 1.0000