LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 200,000 Max Cl/Cd: 69.49 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141f-il-200000.txt Download as CSV file: xf-c141f-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4718 0.08929 0.08557 -0.0273 1.0000 0.0594
-7.750 -0.4898 0.08693 0.08328 -0.0257 1.0000 0.0600
-7.500 -0.5053 0.08373 0.08012 -0.0260 1.0000 0.0608
-7.250 -0.5487 0.07663 0.07269 -0.0337 1.0000 0.0631
-7.000 -0.5447 0.07284 0.06898 -0.0321 1.0000 0.0636
-6.750 -0.5374 0.07068 0.06691 -0.0296 1.0000 0.0641
-6.500 -0.5321 0.06864 0.06490 -0.0276 1.0000 0.0649
-6.250 -0.5277 0.06627 0.06251 -0.0263 1.0000 0.0663
-6.000 -0.5305 0.06114 0.05669 -0.0290 1.0000 0.0716
-5.750 -0.5203 0.05772 0.05342 -0.0278 1.0000 0.0721
-5.500 -0.5098 0.05536 0.05112 -0.0265 1.0000 0.0729
-5.250 -0.4964 0.05316 0.04890 -0.0259 0.9997 0.0743
-5.000 -0.4613 0.04895 0.04400 -0.0307 0.9956 0.0816
-4.750 -0.4347 0.04590 0.04108 -0.0325 0.9931 0.0830
-4.500 -0.4067 0.04382 0.03897 -0.0341 0.9895 0.0863
-4.250 -0.3727 0.04071 0.03537 -0.0370 0.9860 0.0939
-4.000 -0.3424 0.03848 0.03315 -0.0388 0.9831 0.0965
-3.750 -0.3109 0.03694 0.03110 -0.0401 0.9781 0.1064
-3.500 -0.2803 0.03435 0.02860 -0.0420 0.9754 0.1092
-3.250 -0.2372 0.02758 0.02036 -0.0423 0.9744 0.0722
-3.000 -0.1993 0.02581 0.01837 -0.0443 0.9727 0.0700
-2.750 -0.1703 0.02459 0.01687 -0.0443 0.9677 0.0707
-2.500 -0.1354 0.02345 0.01549 -0.0456 0.9643 0.0711
-2.250 -0.0983 0.02214 0.01405 -0.0474 0.9619 0.0720
-2.000 -0.0597 0.02142 0.01339 -0.0498 0.9598 0.0748
-1.750 -0.0320 0.02090 0.01284 -0.0497 0.9538 0.0773
-1.500 0.0028 0.02035 0.01221 -0.0510 0.9498 0.0796
-1.250 0.0410 0.01965 0.01155 -0.0531 0.9470 0.0832
-1.000 0.0816 0.01919 0.01116 -0.0555 0.9433 0.0882
-0.750 0.1119 0.01875 0.01072 -0.0558 0.9348 0.0923
-0.500 0.1555 0.01799 0.01013 -0.0588 0.9308 0.1008
-0.250 0.1887 0.01745 0.00967 -0.0597 0.9239 0.1096
0.000 0.2264 0.01681 0.00917 -0.0614 0.9171 0.1261
0.250 0.2720 0.01566 0.00850 -0.0648 0.9137 0.2256
0.500 0.3335 0.01347 0.00859 -0.0701 0.9141 1.0000
0.750 0.3650 0.01321 0.00826 -0.0704 0.9041 1.0000
1.000 0.4140 0.01268 0.00767 -0.0739 0.8987 1.0000
1.250 0.4437 0.01235 0.00731 -0.0737 0.8885 1.0000
1.500 0.4871 0.01173 0.00666 -0.0758 0.8817 1.0000
1.750 0.5157 0.01124 0.00616 -0.0751 0.8679 1.0000
2.000 0.5462 0.01077 0.00566 -0.0746 0.8528 1.0000
2.250 0.5790 0.01035 0.00521 -0.0747 0.8356 1.0000
2.500 0.6120 0.01003 0.00483 -0.0749 0.8128 1.0000
2.750 0.6401 0.00989 0.00461 -0.0742 0.7839 1.0000
3.000 0.6671 0.00985 0.00445 -0.0733 0.7472 1.0000
3.250 0.6914 0.00995 0.00435 -0.0719 0.6950 1.0000
3.500 0.7107 0.01031 0.00430 -0.0695 0.6116 1.0000
3.750 0.7194 0.01119 0.00447 -0.0653 0.4807 1.0000
4.000 0.7262 0.01232 0.00489 -0.0612 0.3608 1.0000
4.250 0.7411 0.01312 0.00531 -0.0588 0.3043 1.0000
4.500 0.7598 0.01373 0.00571 -0.0571 0.2712 1.0000
4.750 0.7792 0.01432 0.00611 -0.0556 0.2456 1.0000
5.000 0.7998 0.01485 0.00653 -0.0542 0.2212 1.0000
5.250 0.8196 0.01546 0.00699 -0.0528 0.1964 1.0000
5.500 0.8388 0.01617 0.00751 -0.0512 0.1751 1.0000
5.750 0.8596 0.01677 0.00801 -0.0499 0.1596 1.0000
6.000 0.8820 0.01725 0.00848 -0.0488 0.1489 1.0000
6.250 0.9036 0.01788 0.00904 -0.0477 0.1411 1.0000
6.500 0.9260 0.01839 0.00953 -0.0467 0.1346 1.0000
6.750 0.9480 0.01907 0.01015 -0.0457 0.1289 1.0000
7.000 0.9706 0.01952 0.01063 -0.0447 0.1230 1.0000
7.250 0.9925 0.02027 0.01127 -0.0438 0.1177 1.0000
7.500 1.0152 0.02075 0.01185 -0.0429 0.1128 1.0000
7.750 1.0371 0.02138 0.01243 -0.0420 0.1082 1.0000
8.000 1.0598 0.02216 0.01323 -0.0412 0.1037 1.0000
8.250 1.0813 0.02273 0.01384 -0.0402 0.0989 1.0000
8.500 1.1039 0.02370 0.01474 -0.0396 0.0943 1.0000
8.750 1.1239 0.02424 0.01540 -0.0383 0.0893 1.0000
9.000 1.1463 0.02533 0.01638 -0.0378 0.0844 1.0000
9.250 1.1643 0.02589 0.01712 -0.0361 0.0794 1.0000
9.500 1.1853 0.02700 0.01814 -0.0354 0.0747 1.0000
9.750 1.2018 0.02765 0.01896 -0.0336 0.0699 1.0000
10.000 1.2211 0.02875 0.02003 -0.0326 0.0658 1.0000
10.250 1.2367 0.02955 0.02098 -0.0307 0.0619 1.0000
10.500 1.2560 0.03075 0.02212 -0.0297 0.0588 1.0000
10.750 1.2684 0.03167 0.02329 -0.0273 0.0556 1.0000
11.000 1.2840 0.03248 0.02403 -0.0257 0.0533 1.0000
11.250 1.2960 0.03377 0.02553 -0.0235 0.0510 1.0000
11.500 1.3066 0.03481 0.02672 -0.0212 0.0489 1.0000
11.750 1.3208 0.03577 0.02764 -0.0196 0.0474 1.0000
12.000 1.3315 0.03745 0.02951 -0.0175 0.0460 1.0000
12.250 1.3382 0.03917 0.03149 -0.0149 0.0446 1.0000
12.500 1.3455 0.04069 0.03318 -0.0126 0.0435 1.0000
12.750 1.3542 0.04202 0.03456 -0.0106 0.0425 1.0000
13.000 1.3685 0.04356 0.03603 -0.0096 0.0416 1.0000
13.250 1.3612 0.04605 0.03891 -0.0061 0.0410 1.0000
13.500 1.3534 0.04876 0.04196 -0.0031 0.0403 1.0000
13.750 1.3454 0.05155 0.04503 -0.0006 0.0397 1.0000
14.000 1.3377 0.05442 0.04812 0.0015 0.0391 1.0000
14.250 1.3305 0.05735 0.05124 0.0030 0.0387 1.0000
14.500 1.3229 0.06044 0.05450 0.0041 0.0383 1.0000
14.750 1.3122 0.06402 0.05827 0.0048 0.0380 1.0000
15.000 1.2969 0.06839 0.06284 0.0049 0.0378 1.0000
15.250 1.2725 0.07424 0.06896 0.0039 0.0377 1.0000
15.500 1.1716 0.09359 0.08907 -0.0064 0.0390 1.0000
15.750 1.0383 0.12946 0.12543 -0.0308 0.0418 1.0000
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Polar data table (+)
Polar graphs
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