LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 50,000 Max Cl/Cd: 32.59 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141f-il-50000-n5.txt Download as CSV file: xf-c141f-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL958.89 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4295 0.11327 0.10538 -0.0294 1.0000 0.1314
-9.000 -0.4537 0.11185 0.10410 -0.0315 1.0000 0.1342
-8.750 -0.4774 0.11004 0.10244 -0.0325 1.0000 0.1347
-8.500 -0.4550 0.10496 0.09736 -0.0303 1.0000 0.1365
-8.250 -0.4464 0.10166 0.09409 -0.0286 1.0000 0.1387
-8.000 -0.4483 0.09892 0.09142 -0.0275 1.0000 0.1408
-7.750 -0.4564 0.09640 0.08898 -0.0264 1.0000 0.1430
-7.500 -0.4692 0.09384 0.08653 -0.0258 1.0000 0.1454
-7.000 -0.4963 0.08745 0.08027 -0.0275 1.0000 0.1529
-6.500 -0.5071 0.07165 0.06375 -0.0351 1.0000 0.0806
-6.250 -0.5002 0.06853 0.06062 -0.0340 1.0000 0.0799
-6.000 -0.4934 0.06529 0.05732 -0.0331 1.0000 0.0787
-5.750 -0.4860 0.06188 0.05377 -0.0325 1.0000 0.0774
-5.500 -0.4768 0.05839 0.05008 -0.0321 1.0000 0.0763
-5.250 -0.4655 0.05514 0.04658 -0.0317 1.0000 0.0762
-5.000 -0.4522 0.05214 0.04331 -0.0313 1.0000 0.0769
-4.750 -0.4370 0.04928 0.04013 -0.0308 1.0000 0.0775
-4.500 -0.4199 0.04656 0.03708 -0.0303 1.0000 0.0777
-4.250 -0.4012 0.04400 0.03419 -0.0298 1.0000 0.0776
-4.000 -0.3811 0.04169 0.03152 -0.0293 1.0000 0.0781
-3.750 -0.3594 0.03962 0.02896 -0.0288 1.0000 0.0798
-3.500 -0.3370 0.03775 0.02670 -0.0283 1.0000 0.0812
-3.250 -0.3147 0.03618 0.02499 -0.0279 1.0000 0.0824
-3.000 -0.2913 0.03478 0.02337 -0.0275 1.0000 0.0836
-2.750 -0.2677 0.03363 0.02205 -0.0271 1.0000 0.0861
-2.500 -0.2434 0.03256 0.02072 -0.0266 1.0000 0.0889
-2.250 -0.2186 0.03156 0.01942 -0.0261 1.0000 0.0910
-2.000 -0.1944 0.03062 0.01834 -0.0256 1.0000 0.0933
-1.750 -0.1711 0.02990 0.01765 -0.0251 1.0000 0.0970
-1.500 -0.1472 0.02930 0.01695 -0.0245 1.0000 0.1008
-1.250 -0.1128 0.02878 0.01625 -0.0256 0.9962 0.1052
-1.000 -0.0788 0.02825 0.01580 -0.0270 0.9922 0.1114
-0.750 -0.0436 0.02794 0.01536 -0.0285 0.9875 0.1183
-0.500 -0.0082 0.02758 0.01506 -0.0302 0.9833 0.1276
-0.250 0.0251 0.02728 0.01476 -0.0316 0.9776 0.1387
0.000 0.0621 0.02701 0.01457 -0.0338 0.9730 0.1572
0.250 0.0945 0.02658 0.01440 -0.0353 0.9668 0.1914
0.500 0.1255 0.02399 0.01458 -0.0351 0.9622 1.0000
0.750 0.1588 0.02439 0.01466 -0.0364 0.9550 1.0000
1.000 0.1931 0.02480 0.01486 -0.0380 0.9475 1.0000
1.250 0.2250 0.02519 0.01510 -0.0391 0.9393 1.0000
1.500 0.2605 0.02558 0.01539 -0.0410 0.9311 1.0000
1.750 0.2946 0.02581 0.01555 -0.0423 0.9184 1.0000
2.000 0.3381 0.02574 0.01544 -0.0448 0.9009 1.0000
2.250 0.3858 0.02525 0.01493 -0.0474 0.8785 1.0000
2.500 0.4228 0.02479 0.01448 -0.0481 0.8560 1.0000
2.750 0.4583 0.02452 0.01425 -0.0487 0.8393 1.0000
3.000 0.4919 0.02429 0.01408 -0.0490 0.8234 1.0000
3.250 0.5254 0.02395 0.01382 -0.0491 0.8057 1.0000
3.500 0.5581 0.02354 0.01350 -0.0488 0.7859 1.0000
3.750 0.5940 0.02298 0.01304 -0.0488 0.7626 1.0000
4.000 0.6203 0.02263 0.01279 -0.0472 0.7297 1.0000
4.250 0.6501 0.02206 0.01222 -0.0457 0.6779 1.0000
4.500 0.6889 0.02143 0.01124 -0.0451 0.5736 1.0000
4.750 0.7159 0.02197 0.01086 -0.0434 0.4377 1.0000
5.000 0.7304 0.02309 0.01134 -0.0408 0.3633 1.0000
5.250 0.7464 0.02418 0.01204 -0.0389 0.3189 1.0000
5.500 0.7649 0.02517 0.01282 -0.0374 0.2867 1.0000
5.750 0.7844 0.02617 0.01360 -0.0361 0.2613 1.0000
6.000 0.8060 0.02712 0.01446 -0.0352 0.2388 1.0000
6.250 0.8288 0.02809 0.01537 -0.0344 0.2195 1.0000
6.500 0.8535 0.02908 0.01630 -0.0339 0.2031 1.0000
6.750 0.8803 0.03011 0.01725 -0.0338 0.1896 1.0000
7.000 0.9070 0.03111 0.01829 -0.0336 0.1776 1.0000
7.250 0.9347 0.03219 0.01945 -0.0336 0.1674 1.0000
7.500 0.9612 0.03330 0.02047 -0.0334 0.1596 1.0000
7.750 0.9869 0.03447 0.02188 -0.0331 0.1512 1.0000
8.000 1.0116 0.03563 0.02297 -0.0327 0.1450 1.0000
8.250 1.0346 0.03699 0.02459 -0.0320 0.1378 1.0000
8.500 1.0564 0.03814 0.02573 -0.0313 0.1319 1.0000
8.750 1.0759 0.03964 0.02752 -0.0302 0.1252 1.0000
9.000 1.0950 0.04081 0.02870 -0.0291 0.1195 1.0000
9.250 1.1112 0.04249 0.03066 -0.0277 0.1134 1.0000
9.500 1.1279 0.04378 0.03201 -0.0264 0.1080 1.0000
9.750 1.1414 0.04570 0.03420 -0.0247 0.1029 1.0000
10.000 1.1543 0.04742 0.03610 -0.0230 0.0980 1.0000
10.250 1.1674 0.04923 0.03799 -0.0215 0.0940 1.0000
10.500 1.1710 0.05181 0.04102 -0.0189 0.0898 1.0000
10.750 1.1811 0.05363 0.04291 -0.0171 0.0864 1.0000
11.000 1.1836 0.05617 0.04569 -0.0147 0.0835 1.0000
11.250 1.1728 0.05941 0.04937 -0.0110 0.0811 1.0000
11.500 1.1644 0.06230 0.05253 -0.0079 0.0791 1.0000
11.750 1.1611 0.06479 0.05515 -0.0056 0.0771 1.0000
12.000 1.1642 0.06697 0.05734 -0.0039 0.0753 1.0000
12.250 1.1354 0.07166 0.06241 -0.0013 0.0747 1.0000
12.500 1.1043 0.07712 0.06820 -0.0002 0.0743 1.0000
12.750 1.0697 0.08375 0.07511 -0.0010 0.0743 1.0000
13.000 1.0313 0.09215 0.08373 -0.0042 0.0746 1.0000
13.250 0.9891 0.10318 0.09491 -0.0104 0.0751 1.0000
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Polar data table (+)
Polar graphs
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