EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 428 AIRFOIL (e428-il) Reynolds number: 200,000 Max Cl/Cd: 47.95 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e428-il-200000.txt Download as CSV file: xf-e428-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 428 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.9892 0.08577 0.08097 -0.0169 1.0000 0.0268
-14.750 -1.0061 0.07895 0.07400 -0.0213 1.0000 0.0267
-14.500 -1.0205 0.07279 0.06768 -0.0252 1.0000 0.0266
-14.250 -1.0364 0.06654 0.06123 -0.0295 1.0000 0.0267
-14.000 -1.0438 0.06189 0.05645 -0.0320 1.0000 0.0266
-13.750 -1.0539 0.05698 0.05136 -0.0350 1.0000 0.0267
-13.500 -1.0605 0.05276 0.04697 -0.0372 1.0000 0.0267
-13.250 -1.0652 0.04900 0.04304 -0.0390 1.0000 0.0268
-13.000 -1.0658 0.04583 0.03980 -0.0396 1.0000 0.0271
-12.750 -1.0652 0.04299 0.03687 -0.0401 1.0000 0.0272
-12.500 -1.0649 0.04034 0.03418 -0.0404 1.0000 0.0276
-12.250 -1.0645 0.03792 0.03167 -0.0403 1.0000 0.0278
-12.000 -1.0647 0.03582 0.02950 -0.0396 1.0000 0.0283
-11.750 -1.0637 0.03403 0.02763 -0.0380 1.0000 0.0287
-11.500 -1.0584 0.03236 0.02587 -0.0365 1.0000 0.0292
-11.250 -1.0497 0.03075 0.02416 -0.0352 1.0000 0.0299
-11.000 -1.0387 0.02924 0.02250 -0.0340 1.0000 0.0307
-10.750 -1.0270 0.02770 0.02088 -0.0327 1.0000 0.0316
-10.500 -1.0137 0.02629 0.01944 -0.0316 1.0000 0.0330
-10.250 -0.9971 0.02511 0.01819 -0.0307 1.0000 0.0351
-10.000 -0.9806 0.02383 0.01685 -0.0297 1.0000 0.0376
-9.750 -0.9619 0.02274 0.01569 -0.0288 1.0000 0.0415
-9.500 -0.9436 0.02148 0.01438 -0.0279 1.0000 0.0490
-9.250 -0.9262 0.01998 0.01293 -0.0269 1.0000 0.0657
-9.000 -0.9045 0.01921 0.01222 -0.0264 1.0000 0.0819
-8.750 -0.8804 0.01880 0.01175 -0.0259 1.0000 0.0924
-8.500 -0.8563 0.01839 0.01128 -0.0253 1.0000 0.1009
-8.250 -0.8316 0.01810 0.01086 -0.0248 1.0000 0.1100
-8.000 -0.8077 0.01770 0.01046 -0.0243 1.0000 0.1182
-7.750 -0.7837 0.01722 0.00997 -0.0237 1.0000 0.1263
-7.500 -0.7589 0.01688 0.00951 -0.0231 1.0000 0.1350
-7.250 -0.7350 0.01644 0.00913 -0.0225 1.0000 0.1436
-7.000 -0.7105 0.01610 0.00877 -0.0218 1.0000 0.1534
-6.750 -0.6854 0.01594 0.00849 -0.0212 1.0000 0.1641
-6.500 -0.6610 0.01571 0.00832 -0.0206 1.0000 0.1742
-6.250 -0.6364 0.01543 0.00803 -0.0199 1.0000 0.1835
-6.000 -0.6115 0.01526 0.00776 -0.0192 1.0000 0.1928
-5.750 -0.5872 0.01488 0.00745 -0.0185 1.0000 0.2006
-5.500 -0.5623 0.01469 0.00714 -0.0177 1.0000 0.2093
-5.250 -0.5382 0.01430 0.00686 -0.0169 1.0000 0.2171
-5.000 -0.5135 0.01412 0.00656 -0.0162 1.0000 0.2258
-4.750 -0.4896 0.01372 0.00627 -0.0154 1.0000 0.2334
-4.500 -0.4652 0.01356 0.00602 -0.0146 1.0000 0.2425
-4.250 -0.4417 0.01321 0.00579 -0.0137 1.0000 0.2513
-4.000 -0.4182 0.01300 0.00555 -0.0128 1.0000 0.2610
-3.750 -0.3954 0.01275 0.00538 -0.0119 1.0000 0.2704
-3.500 -0.3732 0.01251 0.00517 -0.0108 1.0000 0.2798
-3.250 -0.3520 0.01232 0.00503 -0.0097 1.0000 0.2891
-3.000 -0.3321 0.01211 0.00488 -0.0084 1.0000 0.2973
-2.750 -0.2969 0.01197 0.00477 -0.0102 0.9946 0.3086
-2.500 -0.2469 0.01168 0.00459 -0.0147 0.9833 0.3228
-2.250 -0.1971 0.01135 0.00438 -0.0189 0.9700 0.3395
-2.000 -0.1510 0.01101 0.00415 -0.0223 0.9530 0.3579
-1.750 -0.1092 0.01067 0.00393 -0.0246 0.9293 0.3789
-1.500 -0.0710 0.01033 0.00375 -0.0262 0.9031 0.4062
-1.250 -0.0394 0.01006 0.00362 -0.0263 0.8741 0.4426
-1.000 -0.0129 0.00983 0.00356 -0.0254 0.8446 0.4896
-0.750 0.0117 0.00966 0.00353 -0.0241 0.8167 0.5448
-0.500 0.0357 0.00955 0.00354 -0.0227 0.7895 0.5986
-0.250 0.0595 0.00948 0.00357 -0.0212 0.7632 0.6473
0.000 0.0834 0.00944 0.00358 -0.0197 0.7375 0.6908
0.250 0.1074 0.00940 0.00360 -0.0182 0.7121 0.7301
0.500 0.1311 0.00938 0.00361 -0.0166 0.6860 0.7683
0.750 0.1546 0.00937 0.00363 -0.0149 0.6595 0.8072
1.000 0.1782 0.00936 0.00364 -0.0132 0.6325 0.8466
1.250 0.2047 0.00937 0.00364 -0.0121 0.6026 0.8879
1.500 0.2397 0.00945 0.00363 -0.0128 0.5655 0.9284
1.750 0.2843 0.00962 0.00361 -0.0157 0.5153 0.9627
2.000 0.3302 0.00991 0.00359 -0.0193 0.4505 0.9914
2.250 0.3577 0.01030 0.00363 -0.0195 0.3905 1.0000
2.500 0.3789 0.01070 0.00374 -0.0183 0.3465 1.0000
2.750 0.4016 0.01109 0.00391 -0.0174 0.3174 1.0000
3.000 0.4253 0.01149 0.00412 -0.0166 0.2976 1.0000
3.250 0.4498 0.01187 0.00437 -0.0159 0.2828 1.0000
3.500 0.4747 0.01227 0.00466 -0.0153 0.2707 1.0000
3.750 0.4994 0.01273 0.00496 -0.0146 0.2603 1.0000
4.000 0.5253 0.01304 0.00527 -0.0141 0.2508 1.0000
4.250 0.5507 0.01356 0.00566 -0.0136 0.2432 1.0000
4.500 0.5768 0.01388 0.00601 -0.0131 0.2358 1.0000
4.750 0.6024 0.01439 0.00640 -0.0126 0.2286 1.0000
5.000 0.6286 0.01472 0.00678 -0.0122 0.2215 1.0000
5.250 0.6544 0.01507 0.00709 -0.0117 0.2142 1.0000
5.500 0.6802 0.01549 0.00751 -0.0112 0.2070 1.0000
5.750 0.7062 0.01580 0.00784 -0.0108 0.2003 1.0000
6.000 0.7318 0.01646 0.00838 -0.0104 0.1948 1.0000
6.250 0.7578 0.01673 0.00880 -0.0099 0.1893 1.0000
6.500 0.7835 0.01708 0.00917 -0.0094 0.1835 1.0000
6.750 0.8089 0.01771 0.00973 -0.0090 0.1780 1.0000
7.000 0.8344 0.01800 0.01018 -0.0084 0.1719 1.0000
7.250 0.8597 0.01838 0.01054 -0.0080 0.1662 1.0000
7.500 0.8846 0.01899 0.01120 -0.0074 0.1605 1.0000
7.750 0.9094 0.01929 0.01159 -0.0069 0.1538 1.0000
8.000 0.9337 0.01987 0.01211 -0.0064 0.1475 1.0000
8.250 0.9579 0.02013 0.01253 -0.0057 0.1403 1.0000
8.500 0.9817 0.02071 0.01300 -0.0051 0.1341 1.0000
8.750 1.0054 0.02099 0.01349 -0.0044 0.1273 1.0000
9.000 1.0287 0.02146 0.01387 -0.0038 0.1216 1.0000
9.250 1.0516 0.02202 0.01462 -0.0031 0.1159 1.0000
9.500 1.0745 0.02241 0.01504 -0.0024 0.1108 1.0000
9.750 1.0965 0.02311 0.01578 -0.0016 0.1060 1.0000
10.000 1.1186 0.02360 0.01642 -0.0008 0.1012 1.0000
10.250 1.1398 0.02415 0.01690 -0.0001 0.0968 1.0000
10.500 1.1606 0.02476 0.01771 0.0008 0.0921 1.0000
10.750 1.1810 0.02521 0.01822 0.0017 0.0875 1.0000
11.000 1.1997 0.02597 0.01908 0.0027 0.0829 1.0000
11.250 1.2181 0.02650 0.01971 0.0037 0.0775 1.0000
11.500 1.2338 0.02741 0.02071 0.0049 0.0718 1.0000
11.750 1.2459 0.02846 0.02170 0.0064 0.0658 1.0000
12.000 1.2565 0.02961 0.02302 0.0080 0.0591 1.0000
12.250 1.2603 0.03124 0.02474 0.0102 0.0541 1.0000
12.500 1.2612 0.03276 0.02628 0.0126 0.0508 1.0000
12.750 1.2594 0.03477 0.02837 0.0146 0.0482 1.0000
13.000 1.2590 0.03676 0.03051 0.0160 0.0459 1.0000
13.250 1.2578 0.03898 0.03279 0.0167 0.0442 1.0000
13.500 1.2560 0.04158 0.03538 0.0170 0.0430 1.0000
13.750 1.2522 0.04463 0.03859 0.0169 0.0419 1.0000
14.000 1.2474 0.04800 0.04216 0.0160 0.0408 1.0000
14.250 1.2420 0.05163 0.04596 0.0148 0.0399 1.0000
14.500 1.2369 0.05541 0.04988 0.0133 0.0391 1.0000
14.750 1.2313 0.05940 0.05397 0.0115 0.0384 1.0000
15.000 1.2262 0.06343 0.05806 0.0097 0.0377 1.0000
15.250 1.2241 0.06699 0.06161 0.0085 0.0369 1.0000
15.500 1.2146 0.07194 0.06668 0.0060 0.0364 1.0000
15.750 1.1988 0.07819 0.07314 0.0022 0.0362 1.0000
16.000 1.1811 0.08503 0.08018 -0.0020 0.0359 1.0000
16.250 1.1601 0.09283 0.08819 -0.0069 0.0358 1.0000
16.500 1.1367 0.10157 0.09713 -0.0125 0.0358 1.0000
16.750 1.1064 0.11217 0.10794 -0.0194 0.0359 1.0000
17.000 1.0692 0.12488 0.12083 -0.0276 0.0362 1.0000
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Polar data table (+)
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