Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il) Reynolds number: 100,000 Max Cl/Cd: 47.2 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel430-il-100000.txt Download as CSV file: xf-eiffel430-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 430 (Lachassgne)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2947 0.10116 0.09667 -0.0305 1.0000 0.1098
-9.500 -0.3031 0.09982 0.09545 -0.0303 1.0000 0.1125
-9.250 -0.3284 0.10023 0.09601 -0.0321 0.9970 0.1142
-9.000 -0.3170 0.09562 0.09142 -0.0410 0.9782 0.1155
-8.750 -0.2758 0.08956 0.08533 -0.0394 0.9715 0.1178
-8.500 -0.2493 0.08552 0.08127 -0.0431 0.9557 0.1213
-8.250 -0.2293 0.08182 0.07753 -0.0504 0.9365 0.1264
-8.000 -0.2169 0.07809 0.07369 -0.0630 0.9114 0.1301
-7.750 -0.1858 0.07361 0.06919 -0.0612 0.8953 0.1330
-7.500 -0.1640 0.07046 0.06596 -0.0638 0.8712 0.1377
-7.250 -0.1595 0.06871 0.06392 -0.0731 0.8369 0.1443
-7.000 -0.1414 0.06455 0.05978 -0.0709 0.8097 0.1457
-6.750 -0.1238 0.06167 0.05679 -0.0701 0.7820 0.1483
-6.500 -0.1082 0.05927 0.05422 -0.0707 0.7573 0.1532
-6.250 -0.0949 0.05700 0.05159 -0.0749 0.7381 0.1596
-6.000 -0.0786 0.05401 0.04854 -0.0733 0.7226 0.1618
-5.750 -0.0615 0.05189 0.04628 -0.0728 0.7074 0.1674
-5.500 -0.0436 0.04974 0.04380 -0.0749 0.6964 0.1752
-5.250 -0.0266 0.04721 0.04124 -0.0737 0.6859 0.1784
-4.500 0.0370 0.03584 0.02854 -0.0763 0.6633 0.1311
-4.250 0.0585 0.03336 0.02580 -0.0755 0.6568 0.1253
-4.000 0.0795 0.03076 0.02288 -0.0746 0.6505 0.1220
-3.750 0.1003 0.02641 0.01766 -0.0732 0.6454 0.1164
-3.500 0.1246 0.02524 0.01634 -0.0723 0.6401 0.1184
-3.250 0.1487 0.02441 0.01539 -0.0714 0.6330 0.1229
-3.000 0.1740 0.02282 0.01334 -0.0704 0.6275 0.1282
-2.750 0.1997 0.02194 0.01233 -0.0697 0.6223 0.1328
-2.500 0.2255 0.02136 0.01166 -0.0689 0.6167 0.1408
-2.250 0.2510 0.02101 0.01128 -0.0681 0.6112 0.1507
-2.000 0.2774 0.02053 0.01065 -0.0673 0.6063 0.1639
-1.750 0.3026 0.02024 0.01027 -0.0663 0.6011 0.1864
-1.500 0.3273 0.01967 0.00968 -0.0655 0.5946 0.2111
-1.250 0.3527 0.01929 0.00913 -0.0647 0.5880 0.2338
-1.000 0.3786 0.01866 0.00858 -0.0642 0.5813 0.2517
-0.750 0.4048 0.01814 0.00816 -0.0639 0.5744 0.2714
-0.500 0.4320 0.01770 0.00776 -0.0636 0.5685 0.2903
-0.250 0.4599 0.01730 0.00745 -0.0634 0.5617 0.3036
0.000 0.4904 0.01700 0.00718 -0.0637 0.5535 0.3170
0.250 0.5221 0.01668 0.00697 -0.0643 0.5455 0.3334
0.500 0.5504 0.01644 0.00683 -0.0642 0.5369 0.3509
0.750 0.5765 0.01622 0.00677 -0.0637 0.5281 0.3749
1.000 0.6942 0.01493 0.00684 -0.0825 0.4917 1.0000
1.250 0.7148 0.01515 0.00674 -0.0808 0.4279 1.0000
1.500 0.7309 0.01564 0.00668 -0.0784 0.4012 1.0000
1.750 0.7500 0.01612 0.00686 -0.0766 0.3914 1.0000
2.000 0.7703 0.01656 0.00712 -0.0751 0.3855 1.0000
2.250 0.7917 0.01698 0.00739 -0.0738 0.3820 1.0000
2.500 0.8140 0.01738 0.00765 -0.0727 0.3795 1.0000
2.750 0.8373 0.01777 0.00796 -0.0717 0.3766 1.0000
3.000 0.8609 0.01824 0.00834 -0.0709 0.3725 1.0000
3.250 0.8861 0.01883 0.00876 -0.0704 0.3680 1.0000
3.500 0.9143 0.01951 0.00924 -0.0705 0.3641 1.0000
3.750 0.9396 0.02002 0.00976 -0.0701 0.3600 1.0000
4.000 0.9673 0.02076 0.01038 -0.0701 0.3544 1.0000
4.250 0.9988 0.02183 0.01125 -0.0710 0.3486 1.0000
4.500 1.0222 0.02243 0.01196 -0.0703 0.3438 1.0000
4.750 1.0491 0.02341 0.01289 -0.0704 0.3374 1.0000
5.000 1.0749 0.02455 0.01402 -0.0703 0.3305 1.0000
5.250 1.0986 0.02566 0.01517 -0.0698 0.3221 1.0000
5.500 1.1192 0.02686 0.01648 -0.0688 0.3131 1.0000
5.750 1.1409 0.02840 0.01802 -0.0682 0.3023 1.0000
6.000 1.1613 0.02986 0.01948 -0.0673 0.2903 1.0000
6.250 1.1752 0.03061 0.02045 -0.0650 0.2778 1.0000
6.500 1.1880 0.03140 0.02143 -0.0626 0.2647 1.0000
6.750 1.2005 0.03208 0.02228 -0.0601 0.2520 1.0000
7.000 1.2148 0.03257 0.02285 -0.0579 0.2412 1.0000
7.250 1.2291 0.03271 0.02308 -0.0556 0.2313 1.0000
7.500 1.2399 0.03307 0.02366 -0.0527 0.2207 1.0000
7.750 1.2561 0.03283 0.02336 -0.0507 0.2150 1.0000
8.000 1.2660 0.03325 0.02403 -0.0477 0.2049 1.0000
8.250 1.2796 0.03294 0.02369 -0.0453 0.1999 1.0000
8.500 1.2905 0.03342 0.02437 -0.0426 0.1914 1.0000
8.750 1.3020 0.03316 0.02404 -0.0399 0.1872 1.0000
9.000 1.3134 0.03404 0.02510 -0.0375 0.1799 1.0000
9.250 1.3236 0.03415 0.02517 -0.0347 0.1755 1.0000
9.500 1.3343 0.03496 0.02605 -0.0323 0.1704 1.0000
9.750 1.3436 0.03576 0.02693 -0.0297 0.1654 1.0000
10.000 1.3526 0.03621 0.02727 -0.0270 0.1615 1.0000
10.250 1.3634 0.03762 0.02881 -0.0250 0.1572 1.0000
10.500 1.3736 0.03899 0.03031 -0.0229 0.1532 1.0000
10.750 1.3883 0.04009 0.03141 -0.0215 0.1499 1.0000
11.000 1.4113 0.04169 0.03293 -0.0214 0.1465 1.0000
11.250 1.4134 0.04378 0.03535 -0.0187 0.1441 1.0000
11.500 1.4145 0.04589 0.03772 -0.0161 0.1416 1.0000
11.750 1.4185 0.04781 0.03980 -0.0139 0.1390 1.0000
12.000 1.4299 0.04957 0.04164 -0.0126 0.1365 1.0000
12.250 1.4600 0.05214 0.04412 -0.0138 0.1336 1.0000
12.500 1.4413 0.05496 0.04730 -0.0097 0.1329 1.0000
12.750 1.4173 0.05841 0.05110 -0.0061 0.1322 1.0000
13.000 1.3874 0.06267 0.05568 -0.0031 0.1318 1.0000
13.250 1.3486 0.06820 0.06153 -0.0011 0.1317 1.0000
13.500 1.2960 0.07605 0.06967 -0.0008 0.1322 1.0000
13.750 1.2234 0.08811 0.08199 -0.0037 0.1332 1.0000
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Polar data table (+)
Polar graphs
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