LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Reynolds number: 200,000 Max Cl/Cd: 47.24 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141a-il-200000-n5.txt Download as CSV file: xf-c141a-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8482 0.07735 0.07256 -0.0659 1.0000 0.0241
-15.000 -0.8903 0.06662 0.06150 -0.0727 1.0000 0.0239
-14.750 -0.9093 0.06087 0.05557 -0.0756 1.0000 0.0240
-14.500 -0.9232 0.05640 0.05094 -0.0773 1.0000 0.0242
-14.250 -0.9342 0.05273 0.04713 -0.0779 1.0000 0.0243
-14.000 -0.9438 0.04959 0.04385 -0.0779 1.0000 0.0245
-13.750 -0.9528 0.04684 0.04096 -0.0770 1.0000 0.0248
-13.500 -0.9614 0.04444 0.03842 -0.0755 1.0000 0.0250
-13.250 -0.9699 0.04234 0.03617 -0.0732 1.0000 0.0253
-13.000 -0.9783 0.04049 0.03417 -0.0703 1.0000 0.0256
-12.750 -0.9869 0.03888 0.03241 -0.0668 1.0000 0.0259
-12.500 -0.9961 0.03747 0.03085 -0.0626 1.0000 0.0263
-12.250 -1.0061 0.03625 0.02947 -0.0577 1.0000 0.0266
-12.000 -1.0171 0.03520 0.02827 -0.0523 1.0000 0.0270
-11.750 -1.0278 0.03426 0.02717 -0.0465 1.0000 0.0273
-11.500 -1.0321 0.03327 0.02605 -0.0418 1.0000 0.0277
-11.250 -1.0274 0.03239 0.02514 -0.0387 0.9995 0.0282
-11.000 -1.0068 0.03139 0.02408 -0.0387 0.9970 0.0290
-10.750 -0.9850 0.03037 0.02293 -0.0389 0.9948 0.0301
-10.500 -0.9645 0.02927 0.02163 -0.0386 0.9926 0.0314
-10.250 -0.9447 0.02817 0.02036 -0.0380 0.9901 0.0325
-10.000 -0.9234 0.02731 0.01947 -0.0378 0.9877 0.0335
-9.750 -0.9002 0.02650 0.01858 -0.0378 0.9857 0.0347
-9.500 -0.8751 0.02568 0.01763 -0.0381 0.9840 0.0364
-9.250 -0.8531 0.02489 0.01672 -0.0376 0.9815 0.0380
-9.000 -0.8324 0.02425 0.01606 -0.0370 0.9785 0.0395
-8.750 -0.8092 0.02363 0.01538 -0.0367 0.9762 0.0414
-8.500 -0.7843 0.02301 0.01461 -0.0366 0.9742 0.0435
-8.250 -0.7588 0.02234 0.01395 -0.0369 0.9725 0.0456
-8.000 -0.7306 0.02181 0.01337 -0.0376 0.9711 0.0482
-7.750 -0.7125 0.02135 0.01281 -0.0359 0.9673 0.0505
-7.500 -0.6912 0.02079 0.01227 -0.0352 0.9645 0.0530
-7.250 -0.6659 0.02034 0.01178 -0.0351 0.9622 0.0561
-7.000 -0.6385 0.01988 0.01124 -0.0354 0.9602 0.0594
-6.750 -0.6104 0.01937 0.01076 -0.0360 0.9586 0.0631
-6.500 -0.5800 0.01896 0.01028 -0.0369 0.9573 0.0675
-6.250 -0.5650 0.01856 0.00990 -0.0345 0.9518 0.0711
-6.000 -0.5395 0.01819 0.00952 -0.0344 0.9488 0.0764
-5.750 -0.5119 0.01779 0.00911 -0.0347 0.9465 0.0823
-5.500 -0.4824 0.01744 0.00875 -0.0353 0.9447 0.0899
-5.250 -0.4521 0.01704 0.00840 -0.0362 0.9432 0.0992
-5.000 -0.4321 0.01676 0.00814 -0.0348 0.9393 0.1087
-4.750 -0.4107 0.01648 0.00789 -0.0337 0.9351 0.1206
-4.500 -0.3838 0.01614 0.00762 -0.0338 0.9324 0.1372
-4.250 -0.3548 0.01578 0.00735 -0.0344 0.9303 0.1600
-4.000 -0.3242 0.01537 0.00708 -0.0353 0.9286 0.1911
-3.750 -0.2932 0.01490 0.00682 -0.0363 0.9272 0.2359
-3.500 -0.2825 0.01458 0.00669 -0.0330 0.9203 0.2812
-3.250 -0.2593 0.01398 0.00647 -0.0325 0.9168 0.3635
-3.000 -0.2340 0.01333 0.00628 -0.0323 0.9143 0.4686
-2.750 -0.2057 0.01287 0.00620 -0.0324 0.9125 0.5571
-2.500 -0.1803 0.01266 0.00620 -0.0318 0.9094 0.6157
-2.250 -0.1628 0.01260 0.00627 -0.0295 0.9031 0.6543
-2.000 -0.1336 0.01249 0.00624 -0.0295 0.9002 0.6883
-1.750 -0.1021 0.01238 0.00618 -0.0301 0.8980 0.7157
-1.500 -0.0695 0.01226 0.00610 -0.0308 0.8961 0.7389
-1.250 -0.0488 0.01227 0.00616 -0.0291 0.8902 0.7584
-1.000 -0.0223 0.01221 0.00618 -0.0286 0.8858 0.7797
-0.750 0.0078 0.01213 0.00618 -0.0285 0.8829 0.8065
-0.500 0.0408 0.01206 0.00618 -0.0291 0.8807 0.8274
-0.250 0.0670 0.01205 0.00619 -0.0286 0.8759 0.8407
0.000 0.0935 0.01205 0.00623 -0.0280 0.8702 0.8509
0.250 0.1260 0.01196 0.00616 -0.0288 0.8667 0.8606
0.500 0.1617 0.01186 0.00607 -0.0301 0.8641 0.8693
0.750 0.1866 0.01189 0.00614 -0.0294 0.8571 0.8792
1.000 0.2179 0.01183 0.00611 -0.0298 0.8516 0.8884
1.250 0.2556 0.01168 0.00599 -0.0315 0.8477 0.8953
1.500 0.2840 0.01153 0.00586 -0.0312 0.8348 0.9040
1.750 0.3171 0.01121 0.00553 -0.0316 0.8167 0.9112
2.000 0.3525 0.01100 0.00532 -0.0326 0.7980 0.9174
2.250 0.3809 0.01094 0.00526 -0.0324 0.7782 0.9263
2.500 0.4182 0.01084 0.00513 -0.0340 0.7536 0.9312
2.750 0.4543 0.01076 0.00495 -0.0353 0.7213 0.9371
3.000 0.4884 0.01082 0.00483 -0.0362 0.6798 0.9428
3.250 0.5205 0.01108 0.00486 -0.0369 0.6251 0.9479
3.500 0.5433 0.01150 0.00497 -0.0357 0.5585 0.9568
3.750 0.5678 0.01220 0.00521 -0.0353 0.4644 0.9628
4.000 0.5867 0.01306 0.00557 -0.0339 0.3658 0.9717
4.250 0.6121 0.01392 0.00599 -0.0342 0.2809 0.9778
4.500 0.6388 0.01461 0.00639 -0.0346 0.2241 0.9844
4.750 0.6693 0.01521 0.00677 -0.0358 0.1828 0.9893
5.000 0.6997 0.01575 0.00716 -0.0369 0.1535 0.9944
5.250 0.7321 0.01624 0.00755 -0.0384 0.1308 0.9986
5.500 0.7506 0.01662 0.00787 -0.0369 0.1170 1.0000
5.750 0.7622 0.01695 0.00815 -0.0340 0.1069 1.0000
6.000 0.7741 0.01730 0.00845 -0.0310 0.0981 1.0000
6.250 0.7868 0.01763 0.00878 -0.0282 0.0909 1.0000
6.500 0.7985 0.01804 0.00913 -0.0253 0.0845 1.0000
6.750 0.8121 0.01837 0.00950 -0.0227 0.0789 1.0000
7.000 0.8243 0.01881 0.00989 -0.0199 0.0740 1.0000
7.250 0.8366 0.01918 0.01030 -0.0170 0.0697 1.0000
7.500 0.8486 0.01960 0.01071 -0.0141 0.0658 1.0000
7.750 0.8606 0.02010 0.01119 -0.0114 0.0625 1.0000
8.000 0.8752 0.02055 0.01169 -0.0091 0.0590 1.0000
8.250 0.8895 0.02107 0.01221 -0.0069 0.0559 1.0000
8.500 0.9039 0.02167 0.01283 -0.0047 0.0533 1.0000
8.750 0.9199 0.02222 0.01344 -0.0029 0.0506 1.0000
9.000 0.9354 0.02283 0.01405 -0.0011 0.0482 1.0000
9.250 0.9500 0.02355 0.01479 0.0008 0.0462 1.0000
9.500 0.9663 0.02421 0.01554 0.0025 0.0441 1.0000
9.750 0.9819 0.02489 0.01626 0.0041 0.0421 1.0000
10.000 0.9960 0.02569 0.01706 0.0059 0.0405 1.0000
10.250 1.0113 0.02651 0.01797 0.0075 0.0390 1.0000
10.500 1.0262 0.02736 0.01891 0.0091 0.0375 1.0000
10.750 1.0406 0.02821 0.01983 0.0107 0.0362 1.0000
11.000 1.0538 0.02912 0.02077 0.0123 0.0351 1.0000
11.250 1.0664 0.03017 0.02189 0.0140 0.0340 1.0000
11.500 1.0799 0.03120 0.02306 0.0155 0.0328 1.0000
11.750 1.0923 0.03226 0.02422 0.0171 0.0317 1.0000
12.000 1.1037 0.03335 0.02539 0.0187 0.0308 1.0000
12.250 1.1139 0.03453 0.02663 0.0202 0.0301 1.0000
12.500 1.1229 0.03587 0.02802 0.0218 0.0295 1.0000
12.750 1.1320 0.03737 0.02968 0.0234 0.0289 1.0000
13.000 1.1397 0.03896 0.03146 0.0250 0.0282 1.0000
13.250 1.1460 0.04064 0.03330 0.0266 0.0276 1.0000
13.500 1.1512 0.04237 0.03518 0.0280 0.0270 1.0000
13.750 1.1553 0.04416 0.03709 0.0294 0.0264 1.0000
14.000 1.1587 0.04602 0.03906 0.0306 0.0260 1.0000
14.250 1.1613 0.04801 0.04114 0.0316 0.0256 1.0000
14.500 1.1629 0.05016 0.04335 0.0325 0.0252 1.0000
14.750 1.1611 0.05282 0.04616 0.0332 0.0249 1.0000
15.000 1.1548 0.05610 0.04970 0.0337 0.0245 1.0000
15.250 1.1464 0.05976 0.05360 0.0338 0.0242 1.0000
15.500 1.1359 0.06391 0.05798 0.0333 0.0240 1.0000
15.750 1.1230 0.06862 0.06292 0.0322 0.0238 1.0000
16.000 1.1074 0.07408 0.06861 0.0303 0.0236 1.0000
16.250 1.0884 0.08052 0.07527 0.0274 0.0235 1.0000
16.500 1.0646 0.08830 0.08330 0.0233 0.0234 1.0000
16.750 1.0328 0.09840 0.09367 0.0173 0.0235 1.0000
17.000 0.9763 0.11516 0.11076 0.0068 0.0238 1.0000
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Polar data table (+)
Polar graphs
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