LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 200,000 Max Cl/Cd: 59.34 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141f-il-200000-n5.txt Download as CSV file: xf-c141f-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4899 0.08740 0.08347 -0.0336 1.0000 0.0302
-8.500 -0.5093 0.08384 0.07997 -0.0331 1.0000 0.0303
-8.250 -0.5317 0.08065 0.07684 -0.0324 1.0000 0.0302
-8.000 -0.5436 0.07326 0.06939 -0.0380 0.9980 0.0304
-7.750 -0.5405 0.06328 0.05916 -0.0468 0.9932 0.0306
-7.500 -0.5351 0.05470 0.05024 -0.0517 0.9883 0.0306
-7.250 -0.5153 0.05141 0.04680 -0.0540 0.9856 0.0309
-7.000 -0.4965 0.04804 0.04326 -0.0556 0.9824 0.0313
-6.750 -0.4775 0.04504 0.04007 -0.0566 0.9786 0.0318
-6.500 -0.4561 0.04100 0.03573 -0.0582 0.9755 0.0329
-6.250 -0.4382 0.03293 0.02680 -0.0597 0.9729 0.0340
-6.000 -0.4225 0.02811 0.02123 -0.0588 0.9683 0.0349
-5.750 -0.3948 0.02742 0.02050 -0.0593 0.9652 0.0355
-5.500 -0.3654 0.02647 0.01943 -0.0602 0.9628 0.0364
-5.250 -0.3354 0.02463 0.01725 -0.0611 0.9610 0.0377
-4.750 -0.2808 0.02153 0.01348 -0.0612 0.9551 0.0396
-4.500 -0.2527 0.02094 0.01287 -0.0615 0.9516 0.0404
-4.250 -0.2215 0.02031 0.01217 -0.0623 0.9490 0.0418
-4.000 -0.1889 0.01947 0.01116 -0.0633 0.9471 0.0433
-3.750 -0.1553 0.01865 0.01021 -0.0645 0.9456 0.0445
-3.500 -0.1265 0.01813 0.00971 -0.0647 0.9424 0.0455
-3.250 -0.1019 0.01772 0.00930 -0.0641 0.9370 0.0470
-3.000 -0.0705 0.01722 0.00875 -0.0647 0.9341 0.0490
-2.750 -0.0374 0.01669 0.00824 -0.0658 0.9319 0.0507
-2.500 -0.0029 0.01625 0.00784 -0.0672 0.9301 0.0524
-2.250 0.0324 0.01583 0.00743 -0.0687 0.9287 0.0550
-2.000 0.0502 0.01558 0.00720 -0.0666 0.9202 0.0570
-1.750 0.0821 0.01523 0.00692 -0.0674 0.9170 0.0598
-1.500 0.1161 0.01486 0.00655 -0.0685 0.9144 0.0631
-1.250 0.1444 0.01452 0.00630 -0.0684 0.9085 0.0669
-1.000 0.1724 0.01420 0.00599 -0.0682 0.9012 0.0714
-0.750 0.2072 0.01375 0.00562 -0.0693 0.8970 0.0779
-0.500 0.2300 0.01350 0.00543 -0.0681 0.8869 0.0853
-0.250 0.2632 0.01307 0.00507 -0.0688 0.8813 0.0976
0.000 0.2878 0.01280 0.00487 -0.0678 0.8703 0.1148
0.500 0.3358 0.01032 0.00455 -0.0662 0.8523 0.7212
0.750 0.3676 0.00988 0.00460 -0.0653 0.8413 0.9092
1.000 0.4312 0.00971 0.00441 -0.0721 0.8286 0.9838
1.250 0.4853 0.00954 0.00414 -0.0772 0.8075 1.0000
1.500 0.5147 0.00945 0.00390 -0.0770 0.7783 1.0000
1.750 0.5410 0.00946 0.00373 -0.0762 0.7394 1.0000
2.000 0.5652 0.00959 0.00361 -0.0750 0.6924 1.0000
2.250 0.5857 0.00987 0.00356 -0.0731 0.6293 1.0000
2.500 0.6007 0.01041 0.00361 -0.0702 0.5398 1.0000
2.750 0.6114 0.01120 0.00382 -0.0667 0.4316 1.0000
3.000 0.6244 0.01197 0.00410 -0.0639 0.3438 1.0000
3.250 0.6421 0.01253 0.00437 -0.0620 0.2944 1.0000
3.750 0.6837 0.01334 0.00487 -0.0592 0.2419 1.0000
4.000 0.7056 0.01369 0.00512 -0.0581 0.2238 1.0000
4.250 0.7277 0.01405 0.00539 -0.0570 0.2076 1.0000
4.500 0.7500 0.01441 0.00566 -0.0559 0.1927 1.0000
4.750 0.7728 0.01474 0.00593 -0.0550 0.1783 1.0000
5.000 0.7955 0.01508 0.00623 -0.0540 0.1635 1.0000
5.250 0.8180 0.01545 0.00653 -0.0530 0.1480 1.0000
5.500 0.8403 0.01586 0.00685 -0.0520 0.1332 1.0000
5.750 0.8624 0.01628 0.00721 -0.0509 0.1214 1.0000
6.000 0.8843 0.01672 0.00760 -0.0499 0.1135 1.0000
6.250 0.9059 0.01719 0.00802 -0.0488 0.1075 1.0000
6.500 0.9277 0.01765 0.00847 -0.0477 0.1028 1.0000
6.750 0.9492 0.01812 0.00895 -0.0466 0.0985 1.0000
7.000 0.9698 0.01867 0.00946 -0.0454 0.0944 1.0000
7.250 0.9917 0.01912 0.00994 -0.0444 0.0900 1.0000
7.500 1.0121 0.01967 0.01047 -0.0432 0.0860 1.0000
7.750 1.0329 0.02019 0.01102 -0.0421 0.0827 1.0000
8.000 1.0540 0.02068 0.01156 -0.0410 0.0794 1.0000
8.250 1.0736 0.02128 0.01214 -0.0397 0.0763 1.0000
8.500 1.0940 0.02182 0.01274 -0.0385 0.0732 1.0000
8.750 1.1142 0.02232 0.01330 -0.0373 0.0699 1.0000
9.000 1.1316 0.02296 0.01392 -0.0358 0.0670 1.0000
9.250 1.1514 0.02344 0.01452 -0.0345 0.0637 1.0000
9.500 1.1696 0.02399 0.01511 -0.0331 0.0606 1.0000
9.750 1.1875 0.02459 0.01577 -0.0316 0.0574 1.0000
10.000 1.2056 0.02515 0.01641 -0.0302 0.0541 1.0000
10.250 1.2230 0.02578 0.01711 -0.0287 0.0509 1.0000
10.500 1.2403 0.02639 0.01779 -0.0273 0.0476 1.0000
10.750 1.2566 0.02712 0.01861 -0.0257 0.0446 1.0000
11.000 1.2722 0.02785 0.01939 -0.0241 0.0421 1.0000
11.250 1.2868 0.02871 0.02033 -0.0224 0.0396 1.0000
11.500 1.3007 0.02957 0.02125 -0.0208 0.0375 1.0000
11.750 1.3132 0.03058 0.02232 -0.0189 0.0356 1.0000
12.000 1.3250 0.03162 0.02345 -0.0172 0.0339 1.0000
12.250 1.3349 0.03277 0.02464 -0.0153 0.0327 1.0000
12.500 1.3442 0.03405 0.02605 -0.0134 0.0314 1.0000
12.750 1.3523 0.03541 0.02753 -0.0115 0.0304 1.0000
13.000 1.3590 0.03688 0.02909 -0.0096 0.0295 1.0000
13.250 1.3635 0.03853 0.03082 -0.0077 0.0289 1.0000
13.500 1.3675 0.04034 0.03277 -0.0059 0.0282 1.0000
13.750 1.3705 0.04228 0.03487 -0.0043 0.0276 1.0000
14.000 1.3723 0.04439 0.03712 -0.0029 0.0270 1.0000
14.250 1.3727 0.04669 0.03955 -0.0016 0.0265 1.0000
14.500 1.3719 0.04919 0.04218 -0.0006 0.0261 1.0000
14.750 1.3695 0.05196 0.04507 0.0001 0.0257 1.0000
15.000 1.3652 0.05507 0.04829 0.0005 0.0254 1.0000
15.250 1.3592 0.05854 0.05189 0.0006 0.0251 1.0000
15.500 1.3521 0.06244 0.05600 0.0002 0.0247 1.0000
15.750 1.3429 0.06683 0.06059 -0.0008 0.0245 1.0000
16.000 1.3318 0.07179 0.06575 -0.0023 0.0242 1.0000
16.250 1.3187 0.07742 0.07157 -0.0046 0.0240 1.0000
16.500 1.3030 0.08381 0.07817 -0.0076 0.0238 1.0000
16.750 1.2847 0.09110 0.08565 -0.0114 0.0237 1.0000
17.000 1.2636 0.09934 0.09410 -0.0160 0.0236 1.0000
17.250 1.2387 0.10868 0.10365 -0.0214 0.0236 1.0000
17.500 1.2093 0.11930 0.11448 -0.0276 0.0236 1.0000
17.750 1.1728 0.13190 0.12730 -0.0351 0.0238 1.0000
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Polar data table (+)
Polar graphs
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