NASA SC(2)-0612 AIRFOIL (sc20612-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0612 AIRFOIL (sc20612-il) Reynolds number: 500,000 Max Cl/Cd: 65.04 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20612-il-500000-n5.txt Download as CSV file: xf-sc20612-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0612 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -1.0317 0.10278 0.09919 -0.0339 1.0000 0.0178
-18.000 -1.0651 0.09220 0.08842 -0.0400 1.0000 0.0178
-17.750 -1.0900 0.08343 0.07948 -0.0451 1.0000 0.0178
-17.500 -1.1089 0.07603 0.07191 -0.0494 1.0000 0.0178
-17.250 -1.1231 0.06967 0.06541 -0.0532 1.0000 0.0179
-17.000 -1.1339 0.06420 0.05979 -0.0562 1.0000 0.0180
-16.750 -1.1417 0.05947 0.05492 -0.0587 1.0000 0.0181
-16.500 -1.1470 0.05535 0.05067 -0.0607 1.0000 0.0182
-16.250 -1.1505 0.05171 0.04690 -0.0623 1.0000 0.0184
-16.000 -1.1522 0.04850 0.04358 -0.0634 1.0000 0.0185
-15.750 -1.1527 0.04564 0.04060 -0.0642 1.0000 0.0187
-15.500 -1.1514 0.04306 0.03791 -0.0647 1.0000 0.0189
-15.250 -1.1488 0.04074 0.03548 -0.0650 1.0000 0.0190
-15.000 -1.1448 0.03863 0.03326 -0.0651 1.0000 0.0192
-14.750 -1.1393 0.03674 0.03127 -0.0650 1.0000 0.0194
-14.500 -1.1326 0.03505 0.02947 -0.0647 1.0000 0.0196
-14.250 -1.1261 0.03342 0.02775 -0.0642 1.0000 0.0199
-14.000 -1.1222 0.03170 0.02598 -0.0635 1.0000 0.0202
-13.750 -1.1170 0.03026 0.02449 -0.0625 1.0000 0.0204
-13.500 -1.1119 0.02903 0.02321 -0.0610 1.0000 0.0207
-13.250 -1.1087 0.02796 0.02209 -0.0588 1.0000 0.0210
-13.000 -1.1094 0.02700 0.02109 -0.0558 1.0000 0.0212
-12.750 -1.1055 0.02604 0.02008 -0.0535 1.0000 0.0215
-12.500 -1.0971 0.02511 0.01909 -0.0519 1.0000 0.0218
-12.250 -1.0860 0.02421 0.01814 -0.0507 1.0000 0.0221
-12.000 -1.0724 0.02335 0.01721 -0.0498 1.0000 0.0225
-11.750 -1.0544 0.02251 0.01630 -0.0497 0.9998 0.0230
-11.500 -1.0252 0.02166 0.01537 -0.0515 0.9985 0.0234
-11.250 -0.9963 0.02071 0.01437 -0.0534 0.9972 0.0241
-11.000 -0.9662 0.01992 0.01355 -0.0553 0.9958 0.0248
-10.750 -0.9353 0.01923 0.01283 -0.0571 0.9947 0.0256
-10.500 -0.9039 0.01861 0.01216 -0.0589 0.9937 0.0265
-10.250 -0.8736 0.01804 0.01153 -0.0604 0.9922 0.0275
-10.000 -0.8434 0.01741 0.01088 -0.0618 0.9905 0.0286
-9.750 -0.8124 0.01689 0.01035 -0.0633 0.9888 0.0299
-9.500 -0.7807 0.01640 0.00983 -0.0648 0.9873 0.0313
-9.250 -0.7485 0.01591 0.00931 -0.0665 0.9860 0.0327
-9.000 -0.7160 0.01545 0.00887 -0.0681 0.9849 0.0345
-8.750 -0.6832 0.01506 0.00846 -0.0698 0.9839 0.0367
-8.500 -0.6500 0.01466 0.00805 -0.0715 0.9831 0.0390
-8.250 -0.6165 0.01431 0.00771 -0.0732 0.9824 0.0418
-8.000 -0.5864 0.01399 0.00737 -0.0741 0.9801 0.0441
-7.750 -0.5550 0.01362 0.00701 -0.0754 0.9780 0.0467
-7.500 -0.5224 0.01332 0.00670 -0.0768 0.9762 0.0495
-7.250 -0.4891 0.01299 0.00637 -0.0783 0.9748 0.0523
-7.000 -0.4553 0.01266 0.00606 -0.0800 0.9737 0.0554
-6.750 -0.4209 0.01238 0.00577 -0.0817 0.9726 0.0581
-6.500 -0.3858 0.01205 0.00547 -0.0837 0.9716 0.0615
-6.250 -0.3508 0.01176 0.00519 -0.0855 0.9705 0.0655
-6.000 -0.3158 0.01149 0.00493 -0.0873 0.9696 0.0692
-5.750 -0.2856 0.01123 0.00471 -0.0881 0.9663 0.0746
-5.500 -0.2533 0.01097 0.00449 -0.0893 0.9640 0.0819
-5.250 -0.2199 0.01071 0.00427 -0.0908 0.9619 0.0915
-5.000 -0.1858 0.01042 0.00406 -0.0924 0.9601 0.1039
-4.750 -0.1513 0.01012 0.00384 -0.0941 0.9586 0.1215
-4.500 -0.1163 0.00979 0.00364 -0.0960 0.9572 0.1475
-4.250 -0.0805 0.00941 0.00342 -0.0981 0.9560 0.1851
-4.000 -0.0463 0.00896 0.00322 -0.1001 0.9531 0.2443
-3.750 -0.0106 0.00845 0.00301 -0.1024 0.9503 0.3179
-3.500 0.0265 0.00793 0.00278 -0.1050 0.9479 0.3948
-3.250 0.0646 0.00739 0.00264 -0.1078 0.9460 0.4968
-3.000 0.0987 0.00722 0.00265 -0.1092 0.9433 0.5509
-2.750 0.1309 0.00717 0.00267 -0.1100 0.9397 0.5787
-2.500 0.1605 0.00715 0.00268 -0.1101 0.9326 0.5974
-2.250 0.1918 0.00712 0.00268 -0.1106 0.9269 0.6119
-2.000 0.2209 0.00713 0.00270 -0.1105 0.9173 0.6246
-1.750 0.2499 0.00714 0.00268 -0.1103 0.9020 0.6369
-1.500 0.2779 0.00717 0.00270 -0.1099 0.8831 0.6446
-1.250 0.3064 0.00721 0.00266 -0.1096 0.8605 0.6506
-1.000 0.3345 0.00730 0.00260 -0.1092 0.8267 0.6550
-0.750 0.3616 0.00743 0.00261 -0.1087 0.7877 0.6579
-0.500 0.3879 0.00768 0.00262 -0.1080 0.7331 0.6606
-0.250 0.4132 0.00807 0.00268 -0.1072 0.6556 0.6633
0.000 0.4361 0.00879 0.00286 -0.1062 0.5356 0.6658
0.250 0.4600 0.00953 0.00308 -0.1056 0.4197 0.6682
0.500 0.4857 0.01012 0.00328 -0.1053 0.3305 0.6707
0.750 0.5118 0.01060 0.00347 -0.1051 0.2606 0.6727
1.000 0.5382 0.01101 0.00366 -0.1048 0.2090 0.6746
1.250 0.5652 0.01137 0.00385 -0.1046 0.1673 0.6766
1.500 0.5923 0.01171 0.00405 -0.1045 0.1356 0.6787
1.750 0.6199 0.01198 0.00423 -0.1044 0.1163 0.6807
2.000 0.6477 0.01223 0.00441 -0.1044 0.1016 0.6826
2.250 0.6754 0.01250 0.00460 -0.1043 0.0889 0.6845
2.500 0.7032 0.01275 0.00479 -0.1043 0.0798 0.6864
2.750 0.7309 0.01302 0.00499 -0.1042 0.0727 0.6882
3.000 0.7587 0.01323 0.00520 -0.1041 0.0684 0.6899
3.250 0.7859 0.01347 0.00543 -0.1039 0.0642 0.6915
3.500 0.8131 0.01372 0.00569 -0.1037 0.0612 0.6933
3.750 0.8403 0.01396 0.00595 -0.1035 0.0583 0.6954
4.000 0.8671 0.01425 0.00622 -0.1032 0.0552 0.6977
4.250 0.8941 0.01453 0.00650 -0.1030 0.0527 0.6999
4.500 0.9211 0.01479 0.00678 -0.1027 0.0503 0.7020
4.750 0.9479 0.01509 0.00707 -0.1025 0.0477 0.7040
5.000 0.9745 0.01540 0.00738 -0.1022 0.0453 0.7059
5.500 1.0273 0.01600 0.00799 -0.1016 0.0403 0.7095
5.750 1.0532 0.01631 0.00835 -0.1011 0.0382 0.7115
6.000 1.0790 0.01664 0.00870 -0.1007 0.0361 0.7135
6.250 1.1044 0.01702 0.00908 -0.1002 0.0342 0.7155
6.500 1.1299 0.01738 0.00948 -0.0997 0.0325 0.7175
6.750 1.1551 0.01776 0.00988 -0.0991 0.0309 0.7196
7.000 1.1798 0.01820 0.01032 -0.0986 0.0295 0.7218
7.250 1.2045 0.01865 0.01081 -0.0979 0.0285 0.7239
7.500 1.2289 0.01910 0.01130 -0.0973 0.0276 0.7259
7.750 1.2529 0.01956 0.01180 -0.0966 0.0266 0.7277
8.000 1.2762 0.02006 0.01235 -0.0957 0.0258 0.7296
8.250 1.2985 0.02067 0.01299 -0.0948 0.0250 0.7317
8.500 1.3212 0.02121 0.01361 -0.0938 0.0245 0.7340
8.750 1.3436 0.02176 0.01424 -0.0929 0.0239 0.7364
9.000 1.3657 0.02233 0.01487 -0.0919 0.0232 0.7388
9.250 1.3874 0.02292 0.01551 -0.0908 0.0226 0.7412
9.500 1.4084 0.02354 0.01618 -0.0897 0.0221 0.7435
9.750 1.4282 0.02425 0.01694 -0.0884 0.0216 0.7458
10.000 1.4459 0.02510 0.01786 -0.0868 0.0211 0.7479
10.250 1.4645 0.02582 0.01868 -0.0853 0.0208 0.7502
10.500 1.4824 0.02657 0.01953 -0.0837 0.0205 0.7525
10.750 1.4992 0.02736 0.02043 -0.0819 0.0202 0.7549
11.000 1.5146 0.02818 0.02135 -0.0800 0.0198 0.7574
11.250 1.5285 0.02904 0.02230 -0.0778 0.0195 0.7599
11.500 1.5389 0.02992 0.02327 -0.0751 0.0193 0.7624
11.750 1.5486 0.03085 0.02431 -0.0723 0.0190 0.7645
12.000 1.5585 0.03187 0.02544 -0.0697 0.0188 0.7668
12.250 1.5679 0.03296 0.02664 -0.0673 0.0185 0.7692
12.500 1.5760 0.03417 0.02794 -0.0648 0.0183 0.7718
12.750 1.5827 0.03551 0.02938 -0.0623 0.0181 0.7745
13.000 1.5876 0.03703 0.03100 -0.0598 0.0180 0.7771
13.250 1.5904 0.03878 0.03285 -0.0573 0.0178 0.7796
13.500 1.5900 0.04084 0.03504 -0.0547 0.0176 0.7818
13.750 1.5917 0.04282 0.03717 -0.0526 0.0175 0.7840
14.000 1.5929 0.04493 0.03945 -0.0508 0.0174 0.7864
14.250 1.5927 0.04727 0.04195 -0.0491 0.0172 0.7891
14.500 1.5909 0.04991 0.04475 -0.0478 0.0171 0.7918
14.750 1.5870 0.05291 0.04791 -0.0468 0.0170 0.7945
15.000 1.5810 0.05633 0.05150 -0.0462 0.0168 0.7970
15.250 1.5732 0.06021 0.05556 -0.0462 0.0167 0.7991
15.500 1.5626 0.06474 0.06027 -0.0469 0.0166 0.8013
15.750 1.5488 0.07013 0.06586 -0.0484 0.0165 0.8035
16.000 1.5317 0.07663 0.07256 -0.0512 0.0165 0.8056
16.250 1.5099 0.08467 0.08081 -0.0555 0.0164 0.8076
16.500 1.4817 0.09461 0.09097 -0.0614 0.0164 0.8090
16.750 1.4446 0.10699 0.10360 -0.0691 0.0165 0.8099
17.000 1.3970 0.12190 0.11876 -0.0783 0.0165 0.8100
17.250 1.3325 0.14118 0.13831 -0.0906 0.0167 0.8091
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