LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Reynolds number: 200,000 Max Cl/Cd: 57.42 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-c141c-il-200000-n5.txt Download as CSV file: xf-c141c-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL426.57 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6835 0.07915 0.07516 -0.0486 1.0000 0.0214
-12.000 -0.7340 0.06260 0.05840 -0.0622 1.0000 0.0210
-11.750 -0.7658 0.05538 0.05098 -0.0665 1.0000 0.0209
-11.500 -0.7954 0.05061 0.04600 -0.0663 1.0000 0.0208
-11.250 -0.8244 0.04743 0.04263 -0.0624 1.0000 0.0208
-11.000 -0.8521 0.04502 0.04003 -0.0564 1.0000 0.0209
-10.750 -0.8736 0.04220 0.03691 -0.0511 1.0000 0.0210
-10.500 -0.8890 0.03950 0.03386 -0.0460 1.0000 0.0212
-10.250 -0.8975 0.03702 0.03103 -0.0415 1.0000 0.0214
-10.000 -0.8964 0.03526 0.02912 -0.0381 1.0000 0.0216
-9.750 -0.8912 0.03387 0.02759 -0.0351 1.0000 0.0219
-9.500 -0.8839 0.03259 0.02618 -0.0323 1.0000 0.0223
-9.250 -0.8642 0.03107 0.02446 -0.0321 0.9982 0.0228
-9.000 -0.8410 0.02947 0.02260 -0.0324 0.9959 0.0235
-8.750 -0.8164 0.02789 0.02075 -0.0328 0.9939 0.0243
-8.500 -0.7927 0.02649 0.01904 -0.0328 0.9913 0.0255
-8.250 -0.7678 0.02515 0.01746 -0.0329 0.9888 0.0266
-8.000 -0.7409 0.02420 0.01646 -0.0335 0.9866 0.0276
-7.750 -0.7126 0.02330 0.01546 -0.0343 0.9847 0.0287
-7.500 -0.6848 0.02237 0.01439 -0.0348 0.9828 0.0300
-7.250 -0.6601 0.02149 0.01336 -0.0345 0.9796 0.0314
-7.000 -0.6335 0.02066 0.01244 -0.0348 0.9768 0.0331
-6.750 -0.6048 0.02010 0.01185 -0.0354 0.9744 0.0351
-6.500 -0.5747 0.01948 0.01115 -0.0363 0.9725 0.0376
-6.250 -0.5440 0.01878 0.01034 -0.0372 0.9709 0.0398
-6.000 -0.5211 0.01826 0.00984 -0.0366 0.9668 0.0424
-5.750 -0.4939 0.01782 0.00934 -0.0368 0.9636 0.0458
-5.500 -0.4650 0.01727 0.00876 -0.0373 0.9610 0.0493
-5.250 -0.4340 0.01684 0.00831 -0.0383 0.9590 0.0540
-5.000 -0.4019 0.01639 0.00783 -0.0395 0.9573 0.0591
-4.750 -0.3779 0.01602 0.00747 -0.0389 0.9531 0.0646
-4.500 -0.3514 0.01566 0.00709 -0.0389 0.9492 0.0715
-4.250 -0.3213 0.01531 0.00674 -0.0396 0.9464 0.0804
-4.000 -0.2894 0.01493 0.00642 -0.0407 0.9443 0.0930
-3.750 -0.2563 0.01457 0.00610 -0.0420 0.9426 0.1103
-3.500 -0.2328 0.01424 0.00588 -0.0414 0.9378 0.1322
-3.250 -0.2063 0.01388 0.00566 -0.0413 0.9336 0.1652
-3.000 -0.1769 0.01340 0.00541 -0.0420 0.9307 0.2203
-2.750 -0.1476 0.01275 0.00516 -0.0428 0.9283 0.3129
-2.500 -0.1263 0.01205 0.00500 -0.0418 0.9236 0.4434
-2.250 -0.1056 0.01146 0.00495 -0.0404 0.9185 0.5722
-2.000 -0.0784 0.01110 0.00492 -0.0400 0.9153 0.6619
-1.750 -0.0484 0.01088 0.00489 -0.0401 0.9129 0.7229
-1.500 -0.0250 0.01081 0.00494 -0.0388 0.9073 0.7648
-1.250 0.0026 0.01073 0.00494 -0.0384 0.9030 0.8004
-1.000 0.0337 0.01067 0.00495 -0.0386 0.9000 0.8323
-0.750 0.0673 0.01067 0.00503 -0.0390 0.8978 0.8683
-0.500 0.0959 0.01082 0.00523 -0.0385 0.8926 0.9005
-0.250 0.1291 0.01087 0.00528 -0.0393 0.8882 0.9176
0.000 0.1632 0.01083 0.00522 -0.0404 0.8846 0.9274
0.250 0.2016 0.01078 0.00515 -0.0424 0.8819 0.9341
0.500 0.2305 0.01084 0.00521 -0.0426 0.8744 0.9437
0.750 0.2676 0.01080 0.00518 -0.0444 0.8698 0.9501
1.000 0.3026 0.01074 0.00512 -0.0458 0.8646 0.9574
1.250 0.3393 0.01067 0.00506 -0.0475 0.8548 0.9626
1.500 0.3732 0.01049 0.00487 -0.0484 0.8396 0.9688
1.750 0.4093 0.01027 0.00461 -0.0497 0.8178 0.9727
2.000 0.4450 0.01014 0.00446 -0.0510 0.7949 0.9769
2.250 0.4784 0.01007 0.00435 -0.0520 0.7716 0.9822
2.500 0.5139 0.01002 0.00423 -0.0534 0.7419 0.9858
2.750 0.5481 0.01006 0.00414 -0.0545 0.7025 0.9897
3.000 0.5796 0.01023 0.00410 -0.0551 0.6490 0.9942
3.250 0.6098 0.01062 0.00413 -0.0557 0.5701 0.9982
3.500 0.6280 0.01124 0.00428 -0.0539 0.4748 1.0000
3.750 0.6380 0.01199 0.00455 -0.0507 0.3786 1.0000
4.000 0.6495 0.01270 0.00486 -0.0478 0.3009 1.0000
4.250 0.6626 0.01334 0.00520 -0.0452 0.2385 1.0000
4.500 0.6775 0.01388 0.00551 -0.0430 0.1949 1.0000
4.750 0.6933 0.01437 0.00584 -0.0408 0.1619 1.0000
5.000 0.7100 0.01482 0.00616 -0.0388 0.1376 1.0000
5.250 0.7270 0.01526 0.00652 -0.0369 0.1181 1.0000
5.500 0.7443 0.01569 0.00688 -0.0350 0.1030 1.0000
5.750 0.7619 0.01611 0.00726 -0.0332 0.0907 1.0000
6.000 0.7798 0.01654 0.00766 -0.0314 0.0808 1.0000
6.250 0.7975 0.01702 0.00812 -0.0296 0.0728 1.0000
6.500 0.8157 0.01748 0.00857 -0.0279 0.0655 1.0000
6.750 0.8340 0.01798 0.00907 -0.0262 0.0598 1.0000
7.000 0.8523 0.01850 0.00958 -0.0247 0.0546 1.0000
7.250 0.8705 0.01906 0.01018 -0.0230 0.0504 1.0000
7.500 0.8893 0.01960 0.01076 -0.0215 0.0466 1.0000
7.750 0.9063 0.02030 0.01143 -0.0198 0.0433 1.0000
8.000 0.9253 0.02086 0.01208 -0.0184 0.0405 1.0000
8.250 0.9434 0.02150 0.01278 -0.0169 0.0381 1.0000
8.500 0.9599 0.02229 0.01357 -0.0153 0.0362 1.0000
8.750 0.9770 0.02310 0.01446 -0.0136 0.0345 1.0000
9.000 0.9941 0.02385 0.01530 -0.0120 0.0327 1.0000
9.250 1.0107 0.02458 0.01609 -0.0104 0.0311 1.0000
9.500 1.0260 0.02539 0.01694 -0.0087 0.0298 1.0000
9.750 1.0407 0.02643 0.01803 -0.0069 0.0287 1.0000
10.000 1.0568 0.02743 0.01918 -0.0053 0.0277 1.0000
10.250 1.0722 0.02851 0.02038 -0.0037 0.0268 1.0000
10.500 1.0870 0.02961 0.02160 -0.0020 0.0260 1.0000
10.750 1.1008 0.03072 0.02282 -0.0003 0.0253 1.0000
11.000 1.1135 0.03182 0.02400 0.0014 0.0246 1.0000
11.250 1.1251 0.03307 0.02530 0.0031 0.0240 1.0000
11.500 1.1357 0.03458 0.02696 0.0049 0.0233 1.0000
11.750 1.1452 0.03610 0.02872 0.0068 0.0227 1.0000
12.000 1.1527 0.03777 0.03062 0.0088 0.0221 1.0000
12.250 1.1582 0.03960 0.03267 0.0108 0.0216 1.0000
12.500 1.1617 0.04156 0.03483 0.0128 0.0212 1.0000
12.750 1.1632 0.04365 0.03713 0.0148 0.0209 1.0000
13.000 1.1629 0.04589 0.03957 0.0166 0.0206 1.0000
13.250 1.1607 0.04833 0.04220 0.0182 0.0203 1.0000
13.500 1.1569 0.05099 0.04504 0.0195 0.0201 1.0000
13.750 1.1511 0.05394 0.04817 0.0205 0.0199 1.0000
14.000 1.1434 0.05726 0.05168 0.0210 0.0198 1.0000
14.250 1.1333 0.06105 0.05565 0.0210 0.0196 1.0000
14.500 1.1209 0.06539 0.06018 0.0203 0.0195 1.0000
14.750 1.1056 0.07049 0.06547 0.0188 0.0194 1.0000
15.000 1.0854 0.07682 0.07202 0.0160 0.0194 1.0000
15.250 1.0564 0.08559 0.08107 0.0111 0.0194 1.0000
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