LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.32 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141f-il-1000000-n5.txt Download as CSV file: xf-c141f-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.1289 0.03400 0.03087 -0.0862 0.9953 0.0166
-14.250 -1.1187 0.03138 0.02804 -0.0866 0.9940 0.0168
-14.000 -1.1066 0.02937 0.02586 -0.0863 0.9919 0.0169
-13.750 -1.0908 0.02765 0.02396 -0.0862 0.9902 0.0171
-13.500 -1.0724 0.02613 0.02228 -0.0862 0.9887 0.0173
-13.250 -1.0518 0.02482 0.02082 -0.0863 0.9874 0.0175
-13.000 -1.0298 0.02370 0.01955 -0.0864 0.9864 0.0176
-12.750 -1.0077 0.02258 0.01830 -0.0865 0.9854 0.0178
-12.500 -0.9841 0.02168 0.01733 -0.0866 0.9846 0.0181
-12.250 -0.9613 0.02095 0.01653 -0.0864 0.9833 0.0183
-12.000 -0.9388 0.02029 0.01581 -0.0859 0.9814 0.0185
-11.750 -0.9150 0.01965 0.01510 -0.0857 0.9796 0.0187
-11.500 -0.8904 0.01903 0.01440 -0.0856 0.9781 0.0189
-11.250 -0.8655 0.01842 0.01372 -0.0855 0.9767 0.0191
-11.000 -0.8402 0.01782 0.01304 -0.0854 0.9753 0.0194
-10.750 -0.8147 0.01723 0.01236 -0.0854 0.9740 0.0196
-10.500 -0.7888 0.01667 0.01172 -0.0853 0.9729 0.0199
-10.250 -0.7645 0.01618 0.01115 -0.0849 0.9713 0.0202
-10.000 -0.7402 0.01572 0.01060 -0.0844 0.9694 0.0204
-9.750 -0.7153 0.01524 0.01005 -0.0841 0.9677 0.0206
-9.500 -0.6905 0.01471 0.00947 -0.0837 0.9660 0.0209
-9.250 -0.6647 0.01429 0.00902 -0.0835 0.9644 0.0212
-9.000 -0.6385 0.01392 0.00862 -0.0833 0.9630 0.0215
-8.750 -0.6122 0.01357 0.00823 -0.0831 0.9616 0.0218
-8.500 -0.5856 0.01323 0.00785 -0.0829 0.9602 0.0221
-8.250 -0.5591 0.01290 0.00748 -0.0827 0.9588 0.0224
-8.000 -0.5334 0.01258 0.00712 -0.0823 0.9569 0.0227
-7.750 -0.5073 0.01228 0.00678 -0.0820 0.9550 0.0231
-7.500 -0.4809 0.01199 0.00644 -0.0817 0.9530 0.0235
-7.250 -0.4546 0.01166 0.00608 -0.0814 0.9511 0.0238
-7.000 -0.4282 0.01133 0.00573 -0.0812 0.9491 0.0242
-6.750 -0.4013 0.01106 0.00545 -0.0809 0.9473 0.0246
-6.500 -0.3741 0.01081 0.00519 -0.0808 0.9455 0.0250
-6.250 -0.3470 0.01059 0.00494 -0.0806 0.9436 0.0254
-6.000 -0.3203 0.01035 0.00470 -0.0803 0.9413 0.0259
-5.750 -0.2935 0.01012 0.00445 -0.0800 0.9388 0.0263
-5.500 -0.2663 0.00991 0.00422 -0.0798 0.9362 0.0268
-5.250 -0.2393 0.00967 0.00397 -0.0795 0.9337 0.0274
-5.000 -0.2119 0.00945 0.00376 -0.0793 0.9313 0.0280
-4.750 -0.1841 0.00927 0.00357 -0.0792 0.9290 0.0286
-4.500 -0.1568 0.00909 0.00339 -0.0790 0.9262 0.0292
-4.250 -0.1296 0.00891 0.00321 -0.0788 0.9227 0.0298
-4.000 -0.1021 0.00874 0.00303 -0.0786 0.9192 0.0305
-3.750 -0.0746 0.00854 0.00283 -0.0784 0.9154 0.0312
-3.500 -0.0470 0.00837 0.00267 -0.0782 0.9108 0.0321
-3.250 -0.0198 0.00822 0.00253 -0.0779 0.9035 0.0331
-3.000 0.0079 0.00806 0.00236 -0.0777 0.8969 0.0340
-2.750 0.0355 0.00793 0.00223 -0.0775 0.8886 0.0348
-2.500 0.0630 0.00775 0.00205 -0.0772 0.8786 0.0359
-2.250 0.0906 0.00763 0.00190 -0.0770 0.8661 0.0371
-2.000 0.1182 0.00754 0.00178 -0.0767 0.8527 0.0385
-1.750 0.1454 0.00747 0.00165 -0.0764 0.8366 0.0398
-1.500 0.1723 0.00743 0.00155 -0.0760 0.8185 0.0414
-1.250 0.1994 0.00741 0.00148 -0.0757 0.8020 0.0431
-1.000 0.2264 0.00740 0.00142 -0.0753 0.7838 0.0449
-0.750 0.2526 0.00742 0.00137 -0.0748 0.7580 0.0477
-0.500 0.2780 0.00750 0.00134 -0.0741 0.7246 0.0507
-0.250 0.3023 0.00765 0.00134 -0.0732 0.6789 0.0551
0.000 0.3253 0.00790 0.00137 -0.0721 0.6178 0.0620
0.250 0.3480 0.00821 0.00144 -0.0710 0.5488 0.0715
0.500 0.3707 0.00858 0.00154 -0.0700 0.4711 0.0812
0.750 0.3934 0.00898 0.00166 -0.0690 0.3908 0.0918
1.250 0.4410 0.00959 0.00190 -0.0675 0.2686 0.1307
1.500 0.4631 0.00890 0.00198 -0.0670 0.2353 0.4717
1.750 0.4863 0.00853 0.00209 -0.0662 0.2143 0.6682
2.000 0.5110 0.00842 0.00219 -0.0655 0.2003 0.7549
2.250 0.5335 0.00828 0.00233 -0.0642 0.1905 0.8561
2.500 0.5548 0.00824 0.00246 -0.0623 0.1825 0.9323
2.750 0.5840 0.00838 0.00259 -0.0624 0.1731 0.9691
3.000 0.6187 0.00856 0.00271 -0.0639 0.1615 0.9856
3.250 0.6553 0.00877 0.00284 -0.0658 0.1478 0.9952
3.500 0.6886 0.00903 0.00298 -0.0671 0.1284 0.9986
3.750 0.7145 0.00934 0.00314 -0.0668 0.1048 1.0000
4.000 0.7370 0.00957 0.00330 -0.0657 0.0931 1.0000
4.250 0.7603 0.00979 0.00345 -0.0647 0.0862 1.0000
4.500 0.7845 0.00997 0.00360 -0.0639 0.0822 1.0000
4.750 0.8088 0.01016 0.00377 -0.0631 0.0788 1.0000
5.000 0.8332 0.01038 0.00396 -0.0624 0.0754 1.0000
5.250 0.8582 0.01056 0.00412 -0.0618 0.0731 1.0000
5.500 0.8830 0.01077 0.00431 -0.0611 0.0703 1.0000
5.750 0.9075 0.01102 0.00452 -0.0605 0.0675 1.0000
6.000 0.9326 0.01121 0.00471 -0.0599 0.0654 1.0000
6.250 0.9575 0.01142 0.00490 -0.0593 0.0631 1.0000
6.500 0.9821 0.01166 0.00512 -0.0587 0.0608 1.0000
6.750 1.0067 0.01190 0.00535 -0.0581 0.0590 1.0000
7.000 1.0316 0.01210 0.00556 -0.0575 0.0576 1.0000
7.250 1.0563 0.01233 0.00579 -0.0569 0.0558 1.0000
7.500 1.0805 0.01259 0.00603 -0.0563 0.0536 1.0000
7.750 1.1048 0.01283 0.00627 -0.0557 0.0515 1.0000
8.000 1.1290 0.01308 0.00652 -0.0550 0.0486 1.0000
8.250 1.1528 0.01336 0.00678 -0.0543 0.0457 1.0000
8.500 1.1762 0.01366 0.00706 -0.0536 0.0416 1.0000
8.750 1.1991 0.01400 0.00737 -0.0527 0.0367 1.0000
9.000 1.2212 0.01440 0.00773 -0.0518 0.0320 1.0000
9.250 1.2429 0.01482 0.00813 -0.0508 0.0285 1.0000
9.500 1.2646 0.01523 0.00854 -0.0498 0.0260 1.0000
9.750 1.2860 0.01565 0.00896 -0.0487 0.0241 1.0000
10.000 1.3069 0.01609 0.00940 -0.0476 0.0224 1.0000
10.250 1.3275 0.01651 0.00984 -0.0464 0.0212 1.0000
10.500 1.3472 0.01693 0.01028 -0.0451 0.0201 1.0000
10.750 1.3658 0.01741 0.01077 -0.0436 0.0191 1.0000
11.000 1.3846 0.01785 0.01125 -0.0421 0.0184 1.0000
11.250 1.4032 0.01831 0.01174 -0.0406 0.0177 1.0000
11.500 1.4212 0.01881 0.01227 -0.0391 0.0170 1.0000
11.750 1.4385 0.01936 0.01284 -0.0375 0.0164 1.0000
12.000 1.4554 0.01993 0.01345 -0.0359 0.0159 1.0000
12.250 1.4727 0.02047 0.01403 -0.0344 0.0155 1.0000
12.500 1.4892 0.02104 0.01465 -0.0328 0.0151 1.0000
12.750 1.5051 0.02166 0.01531 -0.0311 0.0148 1.0000
13.000 1.5204 0.02232 0.01602 -0.0294 0.0144 1.0000
13.250 1.5348 0.02303 0.01678 -0.0277 0.0141 1.0000
13.500 1.5483 0.02382 0.01761 -0.0259 0.0138 1.0000
13.750 1.5605 0.02469 0.01853 -0.0240 0.0135 1.0000
14.000 1.5735 0.02549 0.01940 -0.0222 0.0133 1.0000
14.250 1.5858 0.02635 0.02033 -0.0204 0.0132 1.0000
14.500 1.5974 0.02727 0.02132 -0.0187 0.0130 1.0000
14.750 1.6082 0.02825 0.02237 -0.0169 0.0128 1.0000
15.000 1.6182 0.02931 0.02350 -0.0151 0.0126 1.0000
15.250 1.6273 0.03046 0.02472 -0.0134 0.0124 1.0000
15.500 1.6353 0.03171 0.02605 -0.0117 0.0122 1.0000
15.750 1.6424 0.03308 0.02749 -0.0100 0.0120 1.0000
16.000 1.6482 0.03459 0.02907 -0.0084 0.0119 1.0000
16.250 1.6528 0.03625 0.03082 -0.0069 0.0118 1.0000
16.500 1.6560 0.03810 0.03275 -0.0055 0.0116 1.0000
16.750 1.6576 0.04017 0.03492 -0.0042 0.0115 1.0000
17.000 1.6573 0.04249 0.03733 -0.0031 0.0114 1.0000
17.250 1.6547 0.04517 0.04012 -0.0022 0.0113 1.0000
17.500 1.6503 0.04822 0.04328 -0.0017 0.0112 1.0000
17.750 1.6437 0.05168 0.04686 -0.0015 0.0111 1.0000
18.000 1.6383 0.05521 0.05051 -0.0017 0.0111 1.0000
18.250 1.6305 0.05928 0.05470 -0.0024 0.0110 1.0000
18.500 1.6199 0.06397 0.05953 -0.0036 0.0110 1.0000
18.750 1.6050 0.06955 0.06527 -0.0055 0.0110 1.0000
19.000 1.5846 0.07639 0.07227 -0.0084 0.0110 1.0000
19.250 1.5566 0.08500 0.08107 -0.0126 0.0110 1.0000
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Polar data table (+)
Polar graphs
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