LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 100,000 Max Cl/Cd: 46.14 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141f-il-100000-n5.txt Download as CSV file: xf-c141f-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4516 0.09956 0.09407 -0.0336 1.0000 0.0706
-8.500 -0.4677 0.09654 0.09113 -0.0341 1.0000 0.0708
-8.250 -0.4861 0.09366 0.08833 -0.0339 1.0000 0.0709
-8.000 -0.5004 0.09013 0.08484 -0.0345 1.0000 0.0710
-7.500 -0.5210 0.07747 0.07209 -0.0350 1.0000 0.0494
-7.250 -0.5243 0.07413 0.06872 -0.0343 1.0000 0.0492
-7.000 -0.5278 0.07030 0.06482 -0.0341 1.0000 0.0491
-6.750 -0.5292 0.06635 0.06076 -0.0338 1.0000 0.0491
-6.500 -0.5275 0.06256 0.05685 -0.0333 1.0000 0.0489
-6.250 -0.5229 0.05897 0.05312 -0.0326 1.0000 0.0486
-6.000 -0.5162 0.05534 0.04929 -0.0320 1.0000 0.0481
-5.750 -0.4953 0.05075 0.04439 -0.0341 0.9971 0.0478
-5.500 -0.4700 0.04628 0.03952 -0.0365 0.9938 0.0481
-5.250 -0.4451 0.04158 0.03422 -0.0382 0.9901 0.0493
-5.000 -0.4178 0.03758 0.02961 -0.0396 0.9870 0.0497
-4.750 -0.3881 0.03540 0.02719 -0.0411 0.9845 0.0503
-4.500 -0.3609 0.03374 0.02534 -0.0417 0.9808 0.0511
-4.250 -0.3314 0.03225 0.02363 -0.0427 0.9773 0.0528
-4.000 -0.2996 0.03032 0.02128 -0.0439 0.9746 0.0545
-3.750 -0.2663 0.02844 0.01892 -0.0451 0.9724 0.0556
-3.500 -0.2387 0.02719 0.01747 -0.0452 0.9681 0.0568
-3.250 -0.2080 0.02647 0.01673 -0.0462 0.9644 0.0587
-3.000 -0.1745 0.02555 0.01562 -0.0474 0.9615 0.0611
-2.750 -0.1391 0.02452 0.01433 -0.0488 0.9593 0.0629
-2.500 -0.1132 0.02385 0.01369 -0.0485 0.9540 0.0647
-2.250 -0.0819 0.02333 0.01316 -0.0494 0.9498 0.0678
-2.000 -0.0476 0.02272 0.01245 -0.0506 0.9468 0.0709
-1.750 -0.0131 0.02214 0.01196 -0.0520 0.9440 0.0738
-1.500 0.0113 0.02177 0.01163 -0.0514 0.9373 0.0776
-1.250 0.0433 0.02132 0.01120 -0.0523 0.9332 0.0818
-1.000 0.0779 0.02090 0.01089 -0.0537 0.9299 0.0872
-0.750 0.1042 0.02061 0.01063 -0.0534 0.9239 0.0934
-0.500 0.1337 0.02031 0.01040 -0.0538 0.9182 0.1013
-0.250 0.1682 0.01998 0.01014 -0.0551 0.9144 0.1138
0.000 0.1967 0.01969 0.00993 -0.0552 0.9074 0.1317
0.250 0.2301 0.01906 0.00962 -0.0563 0.9001 0.1875
0.500 0.2862 0.01671 0.00973 -0.0603 0.8978 1.0000
0.750 0.3149 0.01653 0.00944 -0.0601 0.8855 1.0000
1.000 0.3478 0.01628 0.00910 -0.0605 0.8744 1.0000
1.250 0.3887 0.01587 0.00861 -0.0623 0.8657 1.0000
1.750 0.4471 0.01530 0.00796 -0.0615 0.8371 1.0000
2.000 0.4777 0.01505 0.00769 -0.0614 0.8223 1.0000
2.250 0.5088 0.01487 0.00750 -0.0614 0.8083 1.0000
2.500 0.5396 0.01471 0.00732 -0.0614 0.7917 1.0000
2.750 0.5709 0.01449 0.00707 -0.0613 0.7669 1.0000
3.000 0.6047 0.01421 0.00667 -0.0614 0.7254 1.0000
3.250 0.6387 0.01408 0.00623 -0.0614 0.6503 1.0000
3.500 0.6658 0.01443 0.00601 -0.0604 0.5399 1.0000
3.750 0.6819 0.01526 0.00616 -0.0578 0.4235 1.0000
4.000 0.6972 0.01615 0.00652 -0.0555 0.3433 1.0000
4.250 0.7155 0.01686 0.00693 -0.0538 0.2984 1.0000
4.500 0.7356 0.01746 0.00734 -0.0524 0.2675 1.0000
4.750 0.7559 0.01805 0.00777 -0.0510 0.2439 1.0000
5.000 0.7769 0.01858 0.00820 -0.0498 0.2240 1.0000
5.250 0.7979 0.01913 0.00867 -0.0486 0.2063 1.0000
5.500 0.8188 0.01970 0.00916 -0.0473 0.1897 1.0000
5.750 0.8397 0.02028 0.00966 -0.0461 0.1742 1.0000
6.000 0.8607 0.02085 0.01020 -0.0449 0.1606 1.0000
6.250 0.8821 0.02143 0.01077 -0.0438 0.1492 1.0000
6.500 0.9030 0.02207 0.01136 -0.0426 0.1403 1.0000
6.750 0.9238 0.02271 0.01197 -0.0414 0.1327 1.0000
7.000 0.9450 0.02339 0.01265 -0.0403 0.1264 1.0000
7.250 0.9660 0.02407 0.01333 -0.0392 0.1209 1.0000
7.500 0.9869 0.02482 0.01406 -0.0381 0.1160 1.0000
7.750 1.0082 0.02553 0.01484 -0.0371 0.1108 1.0000
8.000 1.0278 0.02634 0.01556 -0.0360 0.1062 1.0000
8.250 1.0490 0.02707 0.01642 -0.0350 0.1008 1.0000
8.500 1.0681 0.02786 0.01719 -0.0338 0.0962 1.0000
8.750 1.0882 0.02872 0.01816 -0.0327 0.0915 1.0000
9.000 1.1070 0.02956 0.01904 -0.0314 0.0871 1.0000
9.250 1.1254 0.03054 0.02007 -0.0302 0.0831 1.0000
9.500 1.1434 0.03146 0.02113 -0.0289 0.0787 1.0000
9.750 1.1598 0.03247 0.02208 -0.0275 0.0752 1.0000
10.250 1.1900 0.03449 0.02437 -0.0241 0.0676 1.0000
10.500 1.2035 0.03569 0.02579 -0.0222 0.0639 1.0000
10.750 1.2154 0.03679 0.02697 -0.0202 0.0609 1.0000
11.000 1.2266 0.03804 0.02833 -0.0182 0.0582 1.0000
11.250 1.2365 0.03944 0.02996 -0.0161 0.0552 1.0000
11.500 1.2455 0.04062 0.03119 -0.0141 0.0532 1.0000
11.750 1.2530 0.04236 0.03316 -0.0119 0.0510 1.0000
12.250 1.2642 0.04542 0.03652 -0.0077 0.0475 1.0000
12.500 1.2671 0.04736 0.03864 -0.0056 0.0460 1.0000
12.750 1.2665 0.04978 0.04135 -0.0035 0.0444 1.0000
13.000 1.2659 0.05205 0.04382 -0.0016 0.0433 1.0000
13.250 1.2652 0.05432 0.04622 -0.0001 0.0425 1.0000
13.500 1.2647 0.05656 0.04856 0.0012 0.0418 1.0000
13.750 1.2560 0.06003 0.05227 0.0023 0.0411 1.0000
14.000 1.2400 0.06452 0.05711 0.0029 0.0405 1.0000
14.250 1.2214 0.06960 0.06248 0.0026 0.0400 1.0000
14.500 1.1990 0.07557 0.06874 0.0012 0.0397 1.0000
14.750 1.1702 0.08319 0.07665 -0.0020 0.0396 1.0000
15.000 1.1285 0.09431 0.08808 -0.0084 0.0399 1.0000
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Polar data table (+)
Polar graphs
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