LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 500,000 Max Cl/Cd: 89 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141f-il-500000.txt Download as CSV file: xf-c141f-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4580 0.09849 0.09600 -0.0278 1.0000 0.0326
-9.000 -0.4647 0.09547 0.09301 -0.0275 1.0000 0.0333
-8.500 -0.5444 0.08402 0.08167 -0.0323 1.0000 0.0346
-8.250 -0.5460 0.07694 0.07454 -0.0382 0.9979 0.0349
-8.000 -0.5293 0.07456 0.07216 -0.0395 0.9962 0.0351
-7.750 -0.5106 0.07184 0.06942 -0.0421 0.9945 0.0354
-7.500 -0.4947 0.06840 0.06594 -0.0453 0.9916 0.0359
-7.250 -0.4877 0.05326 0.05018 -0.0585 0.9856 0.0393
-7.000 -0.4642 0.05090 0.04783 -0.0605 0.9844 0.0396
-6.750 -0.4467 0.04900 0.04591 -0.0607 0.9804 0.0399
-6.500 -0.4237 0.04687 0.04372 -0.0621 0.9776 0.0404
-6.250 -0.3979 0.04419 0.04092 -0.0641 0.9755 0.0416
-6.000 -0.3846 0.02958 0.02502 -0.0665 0.9729 0.0397
-5.750 -0.3657 0.02786 0.02323 -0.0653 0.9676 0.0382
-5.500 -0.3425 0.02319 0.01796 -0.0654 0.9648 0.0379
-5.250 -0.3132 0.02032 0.01460 -0.0660 0.9632 0.0383
-5.000 -0.2805 0.01876 0.01267 -0.0671 0.9619 0.0390
-4.750 -0.2473 0.01733 0.01109 -0.0685 0.9610 0.0398
-4.500 -0.2121 0.01679 0.01057 -0.0702 0.9601 0.0408
-4.250 -0.1863 0.01632 0.01008 -0.0697 0.9560 0.0419
-4.000 -0.1572 0.01564 0.00930 -0.0699 0.9525 0.0429
-3.750 -0.1237 0.01504 0.00858 -0.0710 0.9506 0.0439
-3.500 -0.0895 0.01420 0.00772 -0.0724 0.9492 0.0450
-3.250 -0.0536 0.01375 0.00733 -0.0741 0.9480 0.0465
-3.000 -0.0171 0.01333 0.00691 -0.0759 0.9470 0.0483
-2.750 0.0203 0.01290 0.00644 -0.0777 0.9458 0.0497
-2.500 0.0572 0.01217 0.00578 -0.0795 0.9445 0.0517
-2.250 0.0775 0.01190 0.00554 -0.0776 0.9364 0.0534
-2.000 0.1106 0.01156 0.00519 -0.0785 0.9334 0.0558
-1.750 0.1440 0.01101 0.00469 -0.0794 0.9308 0.0585
-1.500 0.1773 0.01067 0.00438 -0.0803 0.9286 0.0615
-1.250 0.1990 0.01040 0.00414 -0.0787 0.9203 0.0644
-1.000 0.2294 0.01006 0.00384 -0.0789 0.9157 0.0689
-0.750 0.2595 0.00968 0.00350 -0.0790 0.9109 0.0743
-0.500 0.2843 0.00945 0.00331 -0.0780 0.9018 0.0810
-0.250 0.3143 0.00905 0.00298 -0.0781 0.8962 0.0956
0.000 0.3387 0.00875 0.00278 -0.0770 0.8845 0.1197
0.250 0.3588 0.00720 0.00254 -0.0760 0.8719 0.5423
0.500 0.3763 0.00621 0.00250 -0.0731 0.8575 0.8226
0.750 0.4000 0.00602 0.00250 -0.0710 0.8416 0.9274
1.000 0.4380 0.00605 0.00248 -0.0725 0.8240 0.9686
1.250 0.4815 0.00615 0.00246 -0.0755 0.8023 0.9854
1.500 0.5338 0.00628 0.00247 -0.0805 0.7740 0.9961
1.750 0.5695 0.00643 0.00244 -0.0820 0.7352 1.0000
2.000 0.5901 0.00663 0.00242 -0.0803 0.6922 1.0000
2.250 0.6086 0.00694 0.00246 -0.0782 0.6348 1.0000
2.500 0.6234 0.00744 0.00257 -0.0754 0.5538 1.0000
2.750 0.6346 0.00821 0.00279 -0.0721 0.4413 1.0000
3.000 0.6474 0.00900 0.00306 -0.0692 0.3374 1.0000
3.250 0.6655 0.00950 0.00329 -0.0673 0.2838 1.0000
3.500 0.6862 0.00985 0.00347 -0.0659 0.2538 1.0000
3.750 0.7081 0.01015 0.00365 -0.0646 0.2329 1.0000
4.000 0.7308 0.01042 0.00384 -0.0636 0.2163 1.0000
4.250 0.7538 0.01069 0.00403 -0.0626 0.2008 1.0000
4.500 0.7770 0.01097 0.00422 -0.0616 0.1843 1.0000
4.750 0.8001 0.01128 0.00443 -0.0607 0.1638 1.0000
5.000 0.8226 0.01165 0.00466 -0.0597 0.1381 1.0000
5.250 0.8447 0.01208 0.00493 -0.0586 0.1193 1.0000
5.500 0.8676 0.01244 0.00523 -0.0576 0.1100 1.0000
5.750 0.8905 0.01281 0.00556 -0.0566 0.1038 1.0000
6.000 0.9135 0.01316 0.00588 -0.0557 0.0987 1.0000
6.250 0.9359 0.01357 0.00625 -0.0547 0.0941 1.0000
6.500 0.9594 0.01388 0.00658 -0.0539 0.0910 1.0000
6.750 0.9821 0.01426 0.00693 -0.0529 0.0877 1.0000
7.000 1.0033 0.01476 0.00741 -0.0517 0.0845 1.0000
7.250 1.0271 0.01503 0.00772 -0.0510 0.0819 1.0000
7.500 1.0500 0.01537 0.00807 -0.0501 0.0791 1.0000
7.750 1.0707 0.01590 0.00856 -0.0489 0.0761 1.0000
8.000 1.0934 0.01624 0.00895 -0.0480 0.0738 1.0000
8.250 1.1164 0.01654 0.00929 -0.0472 0.0711 1.0000
8.500 1.1379 0.01696 0.00969 -0.0462 0.0684 1.0000
8.750 1.1590 0.01741 0.01017 -0.0451 0.0656 1.0000
9.000 1.1820 0.01766 0.01046 -0.0443 0.0624 1.0000
9.250 1.2016 0.01816 0.01092 -0.0430 0.0591 1.0000
9.500 1.2246 0.01833 0.01116 -0.0422 0.0554 1.0000
9.750 1.2448 0.01871 0.01154 -0.0409 0.0516 1.0000
10.000 1.2656 0.01905 0.01187 -0.0398 0.0473 1.0000
10.250 1.2857 0.01947 0.01231 -0.0385 0.0429 1.0000
10.500 1.3040 0.02001 0.01286 -0.0370 0.0393 1.0000
10.750 1.3207 0.02067 0.01350 -0.0354 0.0365 1.0000
11.000 1.3374 0.02131 0.01418 -0.0337 0.0341 1.0000
11.250 1.3513 0.02216 0.01504 -0.0317 0.0323 1.0000
11.500 1.3667 0.02288 0.01583 -0.0299 0.0307 1.0000
11.750 1.3796 0.02377 0.01674 -0.0279 0.0294 1.0000
12.000 1.3901 0.02482 0.01785 -0.0256 0.0284 1.0000
12.250 1.4029 0.02572 0.01884 -0.0236 0.0275 1.0000
12.500 1.4144 0.02670 0.01989 -0.0216 0.0267 1.0000
12.750 1.4241 0.02780 0.02104 -0.0195 0.0260 1.0000
13.000 1.4297 0.02923 0.02251 -0.0170 0.0254 1.0000
13.250 1.4357 0.03066 0.02402 -0.0147 0.0249 1.0000
13.500 1.4445 0.03192 0.02540 -0.0128 0.0245 1.0000
13.750 1.4517 0.03331 0.02690 -0.0109 0.0240 1.0000
14.000 1.4577 0.03483 0.02852 -0.0091 0.0236 1.0000
14.250 1.4626 0.03649 0.03027 -0.0073 0.0232 1.0000
14.500 1.4662 0.03829 0.03215 -0.0057 0.0229 1.0000
14.750 1.4685 0.04028 0.03423 -0.0041 0.0226 1.0000
15.000 1.4688 0.04254 0.03656 -0.0027 0.0223 1.0000
15.250 1.4665 0.04515 0.03925 -0.0014 0.0221 1.0000
15.500 1.4621 0.04810 0.04230 -0.0003 0.0218 1.0000
15.750 1.4615 0.05076 0.04512 0.0003 0.0216 1.0000
16.000 1.4591 0.05372 0.04823 0.0006 0.0215 1.0000
16.250 1.4554 0.05702 0.05168 0.0006 0.0213 1.0000
16.500 1.4504 0.06066 0.05547 0.0002 0.0211 1.0000
16.750 1.4437 0.06467 0.05963 -0.0005 0.0209 1.0000
17.000 1.4356 0.06910 0.06421 -0.0017 0.0208 1.0000
17.250 1.4259 0.07398 0.06925 -0.0034 0.0206 1.0000
17.500 1.4146 0.07932 0.07474 -0.0055 0.0205 1.0000
17.750 1.4018 0.08513 0.08070 -0.0081 0.0204 1.0000
18.000 1.3874 0.09145 0.08718 -0.0111 0.0204 1.0000
18.250 1.3715 0.09827 0.09415 -0.0147 0.0203 1.0000
18.500 1.3540 0.10557 0.10161 -0.0186 0.0203 1.0000
18.750 1.3348 0.11338 0.10958 -0.0230 0.0202 1.0000
19.000 1.3140 0.12174 0.11811 -0.0278 0.0203 1.0000
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Polar data table (+)
Polar graphs
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