LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Reynolds number: 500,000 Max Cl/Cd: 82.35 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141d-il-500000.txt Download as CSV file: xf-c141d-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL610.61 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7522 0.05341 0.05044 -0.0700 1.0000 0.0187
-11.500 -0.7341 0.05423 0.05141 -0.0684 1.0000 0.0190
-11.250 -0.8093 0.04694 0.04369 -0.0649 1.0000 0.0185
-11.000 -0.8403 0.04539 0.04206 -0.0577 1.0000 0.0185
-10.750 -0.8667 0.04271 0.03921 -0.0517 1.0000 0.0184
-10.500 -0.8885 0.03969 0.03595 -0.0462 1.0000 0.0184
-10.250 -0.9041 0.03658 0.03254 -0.0412 1.0000 0.0184
-10.000 -0.9124 0.03371 0.02934 -0.0368 1.0000 0.0184
-9.750 -0.9023 0.03064 0.02583 -0.0357 0.9986 0.0185
-9.500 -0.8834 0.02763 0.02240 -0.0360 0.9964 0.0186
-9.250 -0.8608 0.02519 0.01970 -0.0365 0.9948 0.0189
-9.000 -0.8350 0.02380 0.01818 -0.0371 0.9931 0.0193
-8.750 -0.8089 0.02269 0.01694 -0.0375 0.9908 0.0196
-8.500 -0.7813 0.02162 0.01573 -0.0381 0.9888 0.0201
-8.250 -0.7519 0.02066 0.01463 -0.0389 0.9871 0.0207
-8.000 -0.7213 0.01977 0.01357 -0.0400 0.9857 0.0214
-7.750 -0.6899 0.01891 0.01252 -0.0411 0.9846 0.0220
-7.500 -0.6641 0.01785 0.01144 -0.0412 0.9823 0.0228
-7.250 -0.6369 0.01726 0.01082 -0.0414 0.9793 0.0236
-7.000 -0.6068 0.01666 0.01015 -0.0421 0.9772 0.0246
-6.750 -0.5750 0.01610 0.00949 -0.0431 0.9755 0.0257
-6.500 -0.5436 0.01536 0.00876 -0.0443 0.9742 0.0272
-6.250 -0.5099 0.01495 0.00832 -0.0457 0.9731 0.0291
-6.000 -0.4762 0.01445 0.00781 -0.0472 0.9721 0.0318
-5.750 -0.4545 0.01420 0.00753 -0.0460 0.9669 0.0346
-5.500 -0.4240 0.01374 0.00711 -0.0468 0.9646 0.0385
-5.250 -0.3916 0.01332 0.00668 -0.0479 0.9628 0.0430
-5.000 -0.3570 0.01310 0.00644 -0.0495 0.9614 0.0473
-4.750 -0.3225 0.01271 0.00610 -0.0511 0.9604 0.0524
-4.500 -0.2867 0.01239 0.00579 -0.0530 0.9595 0.0575
-4.250 -0.2517 0.01220 0.00561 -0.0546 0.9583 0.0625
-4.000 -0.2325 0.01194 0.00538 -0.0528 0.9518 0.0673
-3.750 -0.1982 0.01179 0.00523 -0.0542 0.9499 0.0734
-3.500 -0.1649 0.01139 0.00490 -0.0555 0.9481 0.0819
-3.250 -0.1313 0.01102 0.00456 -0.0568 0.9466 0.0919
-3.000 -0.0975 0.01068 0.00427 -0.0581 0.9452 0.1053
-2.750 -0.0751 0.01044 0.00411 -0.0569 0.9395 0.1215
-2.500 -0.0468 0.01005 0.00389 -0.0571 0.9360 0.1620
-2.250 -0.0192 0.00925 0.00363 -0.0574 0.9333 0.2962
-2.000 0.0051 0.00818 0.00338 -0.0571 0.9308 0.5178
-1.750 0.0247 0.00770 0.00336 -0.0553 0.9251 0.6443
-1.500 0.0499 0.00741 0.00330 -0.0545 0.9207 0.7144
-1.250 0.0781 0.00717 0.00321 -0.0542 0.9175 0.7609
-1.000 0.1074 0.00696 0.00312 -0.0541 0.9149 0.8020
-0.750 0.1301 0.00689 0.00317 -0.0526 0.9085 0.8402
-0.500 0.1570 0.00680 0.00315 -0.0520 0.9038 0.8691
-0.250 0.1863 0.00671 0.00309 -0.0518 0.9001 0.8911
0.000 0.2116 0.00673 0.00316 -0.0507 0.8939 0.9157
0.250 0.2392 0.00667 0.00311 -0.0498 0.8858 0.9371
0.500 0.2684 0.00659 0.00300 -0.0493 0.8729 0.9496
0.750 0.2990 0.00655 0.00289 -0.0492 0.8581 0.9597
1.000 0.3360 0.00657 0.00286 -0.0507 0.8444 0.9662
1.250 0.3715 0.00660 0.00284 -0.0521 0.8289 0.9727
1.500 0.4137 0.00664 0.00284 -0.0550 0.8150 0.9760
1.750 0.4505 0.00668 0.00284 -0.0568 0.7986 0.9805
2.000 0.4861 0.00673 0.00283 -0.0584 0.7764 0.9849
2.250 0.5238 0.00680 0.00281 -0.0604 0.7497 0.9880
2.500 0.5585 0.00694 0.00281 -0.0619 0.7111 0.9921
2.750 0.5921 0.00719 0.00284 -0.0631 0.6586 0.9954
3.000 0.6242 0.00765 0.00292 -0.0642 0.5754 0.9986
3.250 0.6446 0.00836 0.00311 -0.0631 0.4625 1.0000
3.500 0.6569 0.00918 0.00337 -0.0604 0.3464 1.0000
3.750 0.6707 0.00987 0.00364 -0.0579 0.2586 1.0000
4.000 0.6860 0.01043 0.00389 -0.0557 0.1976 1.0000
4.250 0.7022 0.01090 0.00413 -0.0536 0.1541 1.0000
4.500 0.7194 0.01129 0.00437 -0.0515 0.1283 1.0000
4.750 0.7374 0.01162 0.00462 -0.0497 0.1141 1.0000
5.000 0.7553 0.01196 0.00489 -0.0477 0.1041 1.0000
5.250 0.7746 0.01220 0.00513 -0.0460 0.0977 1.0000
5.500 0.7921 0.01259 0.00547 -0.0440 0.0907 1.0000
5.750 0.8123 0.01281 0.00571 -0.0425 0.0861 1.0000
6.000 0.8313 0.01314 0.00600 -0.0408 0.0807 1.0000
6.250 0.8506 0.01346 0.00633 -0.0392 0.0759 1.0000
6.500 0.8712 0.01373 0.00659 -0.0378 0.0713 1.0000
6.750 0.8901 0.01415 0.00699 -0.0362 0.0667 1.0000
7.000 0.9120 0.01440 0.00725 -0.0351 0.0626 1.0000
7.250 0.9311 0.01488 0.00770 -0.0335 0.0581 1.0000
7.500 0.9536 0.01513 0.00798 -0.0326 0.0545 1.0000
7.750 0.9730 0.01564 0.00844 -0.0311 0.0506 1.0000
8.000 0.9948 0.01597 0.00882 -0.0301 0.0475 1.0000
8.250 1.0152 0.01641 0.00924 -0.0289 0.0442 1.0000
8.500 1.0354 0.01688 0.00974 -0.0276 0.0414 1.0000
8.750 1.0560 0.01730 0.01017 -0.0265 0.0387 1.0000
9.000 1.0739 0.01796 0.01085 -0.0249 0.0365 1.0000
9.250 1.0936 0.01844 0.01137 -0.0236 0.0345 1.0000
9.500 1.1107 0.01904 0.01197 -0.0219 0.0328 1.0000
9.750 1.1258 0.01983 0.01280 -0.0198 0.0314 1.0000
10.000 1.1433 0.02042 0.01347 -0.0182 0.0301 1.0000
10.250 1.1602 0.02103 0.01412 -0.0166 0.0289 1.0000
10.500 1.1743 0.02190 0.01498 -0.0146 0.0278 1.0000
10.750 1.1887 0.02282 0.01598 -0.0128 0.0269 1.0000
11.000 1.2047 0.02356 0.01682 -0.0111 0.0261 1.0000
11.250 1.2197 0.02437 0.01771 -0.0094 0.0253 1.0000
11.500 1.2339 0.02522 0.01861 -0.0077 0.0247 1.0000
11.750 1.2469 0.02618 0.01961 -0.0059 0.0241 1.0000
12.000 1.2572 0.02752 0.02099 -0.0038 0.0235 1.0000
12.250 1.2676 0.02892 0.02251 -0.0019 0.0231 1.0000
12.500 1.2790 0.03004 0.02377 0.0000 0.0227 1.0000
12.750 1.2891 0.03129 0.02515 0.0018 0.0223 1.0000
13.000 1.2981 0.03264 0.02664 0.0037 0.0220 1.0000
13.250 1.3057 0.03409 0.02822 0.0056 0.0216 1.0000
13.500 1.3122 0.03563 0.02989 0.0074 0.0213 1.0000
13.750 1.3178 0.03725 0.03161 0.0091 0.0210 1.0000
14.000 1.3225 0.03894 0.03341 0.0107 0.0207 1.0000
14.250 1.3264 0.04072 0.03528 0.0122 0.0205 1.0000
14.500 1.3288 0.04272 0.03737 0.0136 0.0202 1.0000
14.750 1.3283 0.04518 0.03992 0.0149 0.0199 1.0000
15.000 1.3218 0.04845 0.04334 0.0163 0.0197 1.0000
15.250 1.3136 0.05183 0.04692 0.0171 0.0196 1.0000
15.500 1.3056 0.05523 0.05052 0.0175 0.0195 1.0000
15.750 1.2951 0.05916 0.05465 0.0173 0.0194 1.0000
16.000 1.2823 0.06368 0.05937 0.0165 0.0194 1.0000
16.250 1.2668 0.06890 0.06479 0.0149 0.0193 1.0000
16.500 1.2490 0.07495 0.07105 0.0124 0.0193 1.0000
16.750 1.2280 0.08202 0.07833 0.0089 0.0193 1.0000
17.000 1.2037 0.09025 0.08676 0.0043 0.0193 1.0000
17.250 1.1757 0.09991 0.09663 -0.0016 0.0193 1.0000
17.500 1.1417 0.11143 0.10834 -0.0088 0.0194 1.0000
17.750 1.0982 0.12580 0.12292 -0.0178 0.0196 1.0000
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Polar data table (+)
Polar graphs
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