EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 433 AIRFOIL (e433-il) Reynolds number: 200,000 Max Cl/Cd: 81.53 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e433-il-200000.txt Download as CSV file: xf-e433-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 433 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2168 0.09933 0.09591 -0.0835 0.9643 0.0397
-9.250 -0.2087 0.09460 0.09119 -0.0887 0.9615 0.0423
-9.000 -0.2077 0.08910 0.08571 -0.0961 0.9571 0.0437
-8.750 -0.1052 0.07343 0.07019 -0.1005 0.9396 0.0508
-8.500 -0.1146 0.06734 0.06411 -0.1065 0.9355 0.0534
-8.250 -0.1192 0.06063 0.05739 -0.1132 0.9330 0.0534
-8.000 -0.2635 0.07187 0.06810 -0.1118 0.9242 0.0445
-7.750 -0.2381 0.06671 0.06323 -0.1120 0.9240 0.0461
-7.500 -0.2266 0.06403 0.06053 -0.1130 0.9203 0.0479
-7.250 -0.2149 0.05995 0.05628 -0.1167 0.9173 0.0511
-7.000 -0.2310 0.05828 0.05454 -0.1123 0.9070 0.0510
-6.750 -0.2291 0.05304 0.04870 -0.1151 0.9027 0.0558
-6.500 -0.2103 0.05120 0.04708 -0.1150 0.8997 0.0593
-6.250 -0.2156 0.04981 0.04559 -0.1110 0.8908 0.0610
-6.000 -0.1975 0.04590 0.04120 -0.1129 0.8881 0.0688
-5.750 -0.1866 0.04415 0.03948 -0.1113 0.8832 0.0715
-5.250 -0.1515 0.03288 0.02652 -0.1076 0.8740 0.0373
-5.000 -0.1142 0.02961 0.02244 -0.1080 0.8729 0.0290
-4.750 -0.0777 0.02674 0.01934 -0.1098 0.8721 0.0281
-4.500 -0.0819 0.02649 0.01899 -0.1041 0.8624 0.0279
-4.250 -0.0491 0.02494 0.01724 -0.1047 0.8604 0.0280
-4.000 -0.0131 0.02376 0.01590 -0.1060 0.8590 0.0290
-3.750 0.0231 0.02223 0.01445 -0.1077 0.8580 0.0321
-3.500 0.0623 0.02119 0.01343 -0.1100 0.8571 0.0394
-3.250 0.0561 0.02159 0.01380 -0.1041 0.8467 0.0438
-3.000 0.0918 0.02013 0.01260 -0.1060 0.8450 0.0914
-2.750 0.1250 0.01734 0.01211 -0.1090 0.8439 0.5872
-2.500 0.1551 0.01764 0.01264 -0.1077 0.8425 0.7381
-2.250 0.1511 0.01850 0.01349 -0.1014 0.8328 0.7589
-2.000 0.1774 0.01877 0.01368 -0.0999 0.8300 0.7855
-1.750 0.2046 0.01895 0.01378 -0.0982 0.8281 0.8057
-1.500 0.2338 0.01901 0.01376 -0.0971 0.8267 0.8232
-1.250 0.2249 0.01969 0.01444 -0.0903 0.8158 0.8339
-1.000 0.2528 0.01960 0.01426 -0.0893 0.8137 0.8479
-0.750 0.2762 0.01949 0.01409 -0.0868 0.8121 0.8651
-0.500 0.2597 0.02009 0.01472 -0.0781 0.8010 0.8806
-0.250 0.2755 0.01980 0.01439 -0.0741 0.7984 0.9003
0.000 0.3109 0.01940 0.01389 -0.0749 0.7971 0.9083
0.250 0.3532 0.01903 0.01343 -0.0776 0.7960 0.9113
0.500 0.3972 0.01864 0.01294 -0.0806 0.7950 0.9137
1.000 0.4342 0.01863 0.01286 -0.0779 0.7821 0.9223
1.250 0.4786 0.01819 0.01236 -0.0809 0.7809 0.9239
1.500 0.4779 0.01855 0.01273 -0.0762 0.7704 0.9304
1.750 0.5222 0.01814 0.01227 -0.0794 0.7685 0.9320
2.000 0.5667 0.01768 0.01176 -0.0825 0.7668 0.9336
2.250 0.6118 0.01719 0.01123 -0.0856 0.7653 0.9352
2.500 0.6150 0.01742 0.01150 -0.0814 0.7550 0.9412
2.750 0.6594 0.01693 0.01098 -0.0845 0.7525 0.9428
3.000 0.7064 0.01644 0.01046 -0.0881 0.7504 0.9442
3.250 0.7147 0.01656 0.01063 -0.0847 0.7406 0.9504
3.500 0.7586 0.01608 0.01014 -0.0877 0.7373 0.9524
3.750 0.7856 0.01594 0.01003 -0.0877 0.7306 0.9566
4.000 0.8173 0.01567 0.00978 -0.0886 0.7241 0.9603
4.250 0.8654 0.01517 0.00925 -0.0923 0.7202 0.9615
4.500 0.8845 0.01516 0.00933 -0.0910 0.7100 0.9680
4.750 0.9298 0.01473 0.00889 -0.0943 0.7046 0.9703
5.000 0.9552 0.01469 0.00893 -0.0942 0.6939 0.9761
5.250 0.9889 0.01454 0.00883 -0.0956 0.6842 0.9808
5.500 1.0298 0.01426 0.00854 -0.0982 0.6753 0.9840
5.750 1.0603 0.01423 0.00858 -0.0991 0.6626 0.9915
6.000 1.0821 0.01418 0.00858 -0.0984 0.6495 1.0000
6.250 1.1027 0.01417 0.00860 -0.0974 0.6358 1.0000
6.500 1.1254 0.01419 0.00864 -0.0967 0.6206 1.0000
6.750 1.1482 0.01425 0.00871 -0.0961 0.6041 1.0000
7.000 1.1716 0.01437 0.00880 -0.0956 0.5859 1.0000
7.250 1.1904 0.01462 0.00905 -0.0944 0.5657 1.0000
7.500 1.2091 0.01494 0.00934 -0.0932 0.5439 1.0000
7.750 1.2269 0.01534 0.00969 -0.0919 0.5210 1.0000
8.000 1.2423 0.01585 0.01012 -0.0902 0.4966 1.0000
8.250 1.2559 0.01644 0.01065 -0.0883 0.4720 1.0000
8.500 1.2678 0.01714 0.01125 -0.0862 0.4471 1.0000
8.750 1.2778 0.01792 0.01197 -0.0838 0.4221 1.0000
9.000 1.2867 0.01878 0.01275 -0.0814 0.3978 1.0000
9.250 1.2945 0.01973 0.01361 -0.0789 0.3742 1.0000
9.500 1.3017 0.02074 0.01457 -0.0764 0.3507 1.0000
9.750 1.3079 0.02186 0.01560 -0.0739 0.3284 1.0000
10.000 1.3141 0.02302 0.01672 -0.0716 0.3060 1.0000
10.250 1.3194 0.02429 0.01792 -0.0692 0.2844 1.0000
10.500 1.3246 0.02562 0.01920 -0.0670 0.2637 1.0000
10.750 1.3297 0.02702 0.02056 -0.0648 0.2427 1.0000
11.000 1.3335 0.02857 0.02203 -0.0627 0.2233 1.0000
11.250 1.3382 0.03012 0.02355 -0.0608 0.2039 1.0000
11.500 1.3426 0.03176 0.02517 -0.0590 0.1853 1.0000
11.750 1.3459 0.03354 0.02690 -0.0572 0.1680 1.0000
12.000 1.3485 0.03544 0.02876 -0.0555 0.1520 1.0000
12.250 1.3508 0.03745 0.03073 -0.0539 0.1371 1.0000
12.750 1.3548 0.04176 0.03499 -0.0510 0.1103 1.0000
13.000 1.3569 0.04403 0.03728 -0.0497 0.0986 1.0000
13.250 1.3590 0.04638 0.03966 -0.0486 0.0881 1.0000
13.500 1.3598 0.04893 0.04226 -0.0476 0.0790 1.0000
13.750 1.3573 0.05187 0.04516 -0.0465 0.0718 1.0000
14.000 1.3598 0.05442 0.04781 -0.0458 0.0648 1.0000
14.250 1.3587 0.05742 0.05085 -0.0451 0.0591 1.0000
14.500 1.3595 0.06028 0.05379 -0.0446 0.0540 1.0000
14.750 1.3579 0.06348 0.05702 -0.0441 0.0499 1.0000
15.000 1.3596 0.06642 0.06008 -0.0440 0.0458 1.0000
15.250 1.3570 0.06985 0.06348 -0.0437 0.0425 1.0000
15.500 1.3589 0.07291 0.06674 -0.0437 0.0395 1.0000
15.750 1.3590 0.07623 0.07016 -0.0439 0.0367 1.0000
16.000 1.3584 0.07954 0.07342 -0.0438 0.0341 1.0000
16.250 1.3581 0.08314 0.07727 -0.0443 0.0320 1.0000
16.500 1.3568 0.08686 0.08110 -0.0451 0.0297 1.0000
16.750 1.3564 0.09027 0.08447 -0.0455 0.0276 1.0000
17.000 1.3539 0.09434 0.08877 -0.0464 0.0259 1.0000
17.250 1.3507 0.09857 0.09317 -0.0477 0.0242 1.0000
17.500 1.3484 0.10259 0.09721 -0.0491 0.0227 1.0000
17.750 1.3451 0.10677 0.10150 -0.0502 0.0211 1.0000
18.000 1.3392 0.11172 0.10668 -0.0523 0.0198 1.0000
18.250 1.3348 0.11637 0.11144 -0.0544 0.0186 1.0000
18.500 1.3342 0.12004 0.11506 -0.0559 0.0173 1.0000
18.750 1.3251 0.12580 0.12107 -0.0587 0.0164 1.0000
19.000 1.3175 0.13136 0.12686 -0.0616 0.0156 1.0000
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