LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Reynolds number: 100,000 Max Cl/Cd: 45.14 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141b-il-100000.txt Download as CSV file: xf-c141b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL113.6 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5422 0.09402 0.08872 -0.0368 1.0000 0.1764
-9.500 -0.5391 0.09123 0.08595 -0.0352 1.0000 0.1801
-9.250 -0.8253 0.06109 0.05479 -0.0335 1.0000 0.0845
-9.000 -0.8275 0.05726 0.05086 -0.0307 1.0000 0.0836
-8.750 -0.8331 0.05361 0.04699 -0.0273 1.0000 0.0829
-8.500 -0.8384 0.05011 0.04315 -0.0235 1.0000 0.0828
-8.250 -0.8405 0.04688 0.03949 -0.0198 1.0000 0.0834
-8.000 -0.8392 0.04394 0.03606 -0.0163 1.0000 0.0843
-7.750 -0.8339 0.04141 0.03299 -0.0130 1.0000 0.0851
-7.500 -0.8221 0.03804 0.02943 -0.0112 1.0000 0.0866
-7.250 -0.8050 0.03649 0.02792 -0.0099 1.0000 0.0897
-7.000 -0.7896 0.03486 0.02603 -0.0080 1.0000 0.0932
-6.750 -0.7734 0.03302 0.02374 -0.0060 1.0000 0.0962
-6.500 -0.7549 0.03111 0.02156 -0.0046 1.0000 0.0999
-6.250 -0.7345 0.02992 0.02036 -0.0036 1.0000 0.1046
-6.000 -0.7136 0.02873 0.01889 -0.0023 1.0000 0.1095
-5.750 -0.6918 0.02735 0.01743 -0.0014 1.0000 0.1151
-5.500 -0.6701 0.02641 0.01644 -0.0004 1.0000 0.1215
-5.250 -0.6478 0.02535 0.01527 0.0005 1.0000 0.1287
-5.000 -0.6260 0.02453 0.01447 0.0015 1.0000 0.1374
-4.750 -0.6040 0.02360 0.01360 0.0024 1.0000 0.1471
-4.500 -0.5823 0.02283 0.01284 0.0034 1.0000 0.1595
-4.250 -0.5611 0.02207 0.01218 0.0044 1.0000 0.1752
-4.000 -0.5405 0.02128 0.01158 0.0054 1.0000 0.1959
-3.750 -0.5202 0.02044 0.01101 0.0064 1.0000 0.2281
-3.500 -0.5007 0.01930 0.01044 0.0075 1.0000 0.2965
-3.250 -0.4866 0.01754 0.01036 0.0100 1.0000 0.5624
-3.000 -0.4716 0.01744 0.01080 0.0138 1.0000 0.7097
-2.750 -0.4552 0.01763 0.01114 0.0172 1.0000 0.7773
-2.500 -0.4383 0.01795 0.01152 0.0205 1.0000 0.8275
-2.250 -0.4190 0.01839 0.01195 0.0234 1.0000 0.8702
-2.000 -0.3926 0.01898 0.01248 0.0247 1.0000 0.9087
-1.750 -0.3477 0.01986 0.01323 0.0222 1.0000 0.9412
-1.500 -0.2738 0.02102 0.01418 0.0136 1.0000 0.9639
-1.250 -0.1856 0.02206 0.01502 0.0017 1.0000 0.9841
-1.000 -0.1002 0.02267 0.01546 -0.0103 1.0000 1.0000
-0.750 -0.1046 0.02233 0.01509 -0.0064 1.0000 1.0000
-0.500 -0.1094 0.02201 0.01474 -0.0024 1.0000 1.0000
-0.250 -0.1135 0.02174 0.01443 0.0016 1.0000 1.0000
0.000 -0.1086 0.02164 0.01428 0.0041 0.9990 1.0000
0.250 -0.0663 0.02212 0.01469 -0.0001 0.9909 1.0000
0.500 -0.0249 0.02264 0.01516 -0.0040 0.9830 1.0000
0.750 0.0113 0.02300 0.01548 -0.0068 0.9735 1.0000
1.000 0.0454 0.02336 0.01581 -0.0091 0.9635 1.0000
1.250 0.0834 0.02380 0.01623 -0.0121 0.9545 1.0000
1.500 0.1204 0.02416 0.01659 -0.0147 0.9446 1.0000
1.750 0.1519 0.02444 0.01687 -0.0161 0.9330 1.0000
2.000 0.1909 0.02475 0.01721 -0.0188 0.9225 1.0000
2.250 0.2403 0.02495 0.01746 -0.0231 0.9123 1.0000
2.500 0.2850 0.02484 0.01741 -0.0262 0.8975 1.0000
2.750 0.3422 0.02436 0.01703 -0.0309 0.8817 1.0000
3.000 0.3954 0.02372 0.01651 -0.0347 0.8663 1.0000
3.250 0.4459 0.02298 0.01590 -0.0379 0.8515 1.0000
3.500 0.5012 0.02194 0.01502 -0.0415 0.8367 1.0000
3.750 0.5597 0.02054 0.01381 -0.0453 0.8212 1.0000
4.000 0.6100 0.01903 0.01248 -0.0473 0.8024 1.0000
4.250 0.6400 0.01799 0.01155 -0.0458 0.7762 1.0000
4.500 0.6761 0.01685 0.01049 -0.0453 0.7378 1.0000
4.750 0.7186 0.01592 0.00941 -0.0457 0.6564 1.0000
5.000 0.7369 0.01639 0.00892 -0.0422 0.4763 1.0000
5.250 0.7303 0.01789 0.00937 -0.0356 0.3330 1.0000
5.500 0.7310 0.01925 0.01008 -0.0307 0.2620 1.0000
5.750 0.7388 0.02038 0.01085 -0.0271 0.2224 1.0000
6.000 0.7508 0.02143 0.01162 -0.0243 0.1955 1.0000
6.250 0.7672 0.02246 0.01248 -0.0223 0.1749 1.0000
6.500 0.7860 0.02349 0.01339 -0.0207 0.1585 1.0000
6.750 0.8079 0.02465 0.01442 -0.0197 0.1452 1.0000
7.000 0.8298 0.02569 0.01539 -0.0187 0.1339 1.0000
7.250 0.8534 0.02689 0.01668 -0.0179 0.1245 1.0000
7.500 0.8803 0.02842 0.01810 -0.0180 0.1162 1.0000
7.750 0.9015 0.02957 0.01944 -0.0167 0.1095 1.0000
8.000 0.9286 0.03142 0.02116 -0.0170 0.1031 1.0000
8.250 0.9469 0.03278 0.02286 -0.0150 0.0985 1.0000
8.500 0.9669 0.03415 0.02432 -0.0138 0.0938 1.0000
8.750 0.9887 0.03649 0.02672 -0.0132 0.0899 1.0000
9.000 1.0007 0.03838 0.02906 -0.0104 0.0874 1.0000
9.250 1.0128 0.04036 0.03135 -0.0079 0.0844 1.0000
9.500 1.0296 0.04206 0.03314 -0.0065 0.0814 1.0000
9.750 1.0462 0.04479 0.03591 -0.0054 0.0792 1.0000
10.000 1.0514 0.04821 0.03967 -0.0025 0.0784 1.0000
10.250 1.0498 0.05107 0.04298 0.0015 0.0779 1.0000
10.500 1.0441 0.05414 0.04646 0.0056 0.0774 1.0000
10.750 1.0346 0.05739 0.05008 0.0099 0.0771 1.0000
11.000 1.0215 0.06077 0.05378 0.0141 0.0770 1.0000
11.250 1.0045 0.06412 0.05739 0.0184 0.0770 1.0000
11.500 0.9852 0.06762 0.06110 0.0224 0.0772 1.0000
11.750 0.9664 0.07152 0.06517 0.0253 0.0776 1.0000
12.000 0.9522 0.07597 0.06974 0.0271 0.0781 1.0000
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Polar data table (+)
Polar graphs
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