Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.58 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel430-il-1000000.txt Download as CSV file: xf-eiffel430-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2278 0.09360 0.08911 -0.0699 0.2808 0.0291
-11.250 -0.2191 0.09170 0.08721 -0.0702 0.2796 0.0295
-11.000 -0.5927 0.02737 0.02208 -0.0949 0.3026 0.0287
-10.750 -0.5820 0.02526 0.01975 -0.0931 0.3002 0.0290
-10.500 -0.5642 0.02418 0.01855 -0.0918 0.2974 0.0292
-10.250 -0.5439 0.02346 0.01774 -0.0906 0.2945 0.0295
-10.000 -0.5222 0.02293 0.01713 -0.0896 0.2915 0.0298
-9.750 -0.5013 0.02221 0.01629 -0.0884 0.2894 0.0301
-9.500 -0.4809 0.02133 0.01529 -0.0872 0.2881 0.0304
-9.250 -0.4600 0.02050 0.01433 -0.0860 0.2864 0.0307
-9.000 -0.4392 0.01960 0.01328 -0.0847 0.2847 0.0310
-8.750 -0.4174 0.01884 0.01237 -0.0835 0.2829 0.0314
-8.500 -0.3952 0.01813 0.01152 -0.0823 0.2811 0.0317
-8.250 -0.3725 0.01748 0.01074 -0.0812 0.2795 0.0320
-8.000 -0.3491 0.01697 0.01011 -0.0802 0.2777 0.0324
-7.750 -0.3253 0.01659 0.00962 -0.0792 0.2755 0.0326
-7.500 -0.3004 0.01626 0.00919 -0.0783 0.2749 0.0329
-7.250 -0.2789 0.01515 0.00795 -0.0770 0.2742 0.0334
-7.000 -0.2546 0.01466 0.00742 -0.0762 0.2733 0.0340
-6.750 -0.2294 0.01436 0.00709 -0.0754 0.2724 0.0345
-6.500 -0.2040 0.01409 0.00677 -0.0746 0.2713 0.0350
-6.250 -0.1785 0.01382 0.00645 -0.0739 0.2703 0.0354
-6.000 -0.1530 0.01355 0.00614 -0.0731 0.2692 0.0360
-5.750 -0.1274 0.01330 0.00583 -0.0724 0.2682 0.0365
-5.500 -0.1017 0.01308 0.00556 -0.0717 0.2671 0.0371
-5.250 -0.0758 0.01290 0.00534 -0.0710 0.2661 0.0376
-5.000 -0.0498 0.01277 0.00517 -0.0703 0.2651 0.0380
-4.750 -0.0254 0.01233 0.00468 -0.0694 0.2640 0.0389
-4.500 -0.0004 0.01213 0.00446 -0.0686 0.2629 0.0398
-4.250 0.0247 0.01207 0.00440 -0.0678 0.2614 0.0407
-4.000 0.0501 0.01203 0.00434 -0.0670 0.2602 0.0417
-3.750 0.0764 0.01190 0.00420 -0.0664 0.2597 0.0427
-3.500 0.1030 0.01177 0.00405 -0.0659 0.2588 0.0435
-3.250 0.1293 0.01165 0.00390 -0.0653 0.2579 0.0443
-3.000 0.1545 0.01139 0.00364 -0.0645 0.2571 0.0462
-2.750 0.1804 0.01130 0.00355 -0.0639 0.2563 0.0478
-2.500 0.2063 0.01124 0.00348 -0.0632 0.2555 0.0494
-2.250 0.2323 0.01121 0.00343 -0.0626 0.2547 0.0508
-2.000 0.2576 0.01108 0.00331 -0.0619 0.2539 0.0541
-1.750 0.2831 0.01102 0.00325 -0.0612 0.2531 0.0569
-1.500 0.3088 0.01097 0.00319 -0.0605 0.2521 0.0606
-1.250 0.3341 0.01084 0.00313 -0.0598 0.2509 0.0749
-1.000 0.3591 0.01076 0.00315 -0.0591 0.2500 0.1065
-0.750 0.3847 0.01074 0.00316 -0.0584 0.2487 0.1199
-0.500 0.4097 0.01078 0.00323 -0.0577 0.2475 0.1314
-0.250 0.4339 0.01090 0.00340 -0.0569 0.2460 0.1458
0.000 0.4581 0.01108 0.00361 -0.0560 0.2448 0.1588
0.250 0.4846 0.01113 0.00370 -0.0556 0.2444 0.1692
0.500 0.5111 0.01119 0.00376 -0.0551 0.2439 0.1755
0.750 0.5374 0.01124 0.00384 -0.0547 0.2433 0.1813
1.000 0.5637 0.01131 0.00392 -0.0542 0.2425 0.1859
1.250 0.5900 0.01140 0.00400 -0.0538 0.2416 0.1886
1.500 0.6154 0.01139 0.00403 -0.0532 0.2407 0.1931
1.750 0.6412 0.01144 0.00410 -0.0527 0.2396 0.1969
2.000 0.6671 0.01149 0.00416 -0.0523 0.2385 0.2005
2.250 0.6933 0.01155 0.00422 -0.0518 0.2372 0.2033
2.500 0.7187 0.01152 0.00421 -0.0513 0.2359 0.2065
2.750 0.7448 0.01149 0.00418 -0.0509 0.2342 0.2090
3.000 0.7702 0.01151 0.00422 -0.0504 0.2326 0.2113
3.250 0.7932 0.01167 0.00437 -0.0494 0.2294 0.2133
3.500 0.8213 0.01156 0.00428 -0.0494 0.2280 0.2152
3.750 0.8485 0.01150 0.00425 -0.0493 0.2257 0.2173
4.000 0.8753 0.01146 0.00423 -0.0490 0.2227 0.2192
4.250 0.9019 0.01140 0.00417 -0.0488 0.2188 0.2230
4.500 0.9273 0.01142 0.00418 -0.0483 0.2143 0.2250
4.750 0.9528 0.01143 0.00424 -0.0479 0.2104 0.2274
5.000 0.9784 0.01144 0.00421 -0.0475 0.1994 0.2294
5.250 0.9925 0.01195 0.00441 -0.0451 0.1453 0.2311
5.500 1.0062 0.01247 0.00482 -0.0426 0.1270 0.2332
5.750 1.0239 0.01277 0.00512 -0.0407 0.1197 0.2387
6.000 1.0435 0.01298 0.00537 -0.0393 0.1170 0.2440
6.250 1.1318 0.01244 0.00633 -0.0539 0.1104 0.9781
6.500 1.1691 0.01297 0.00685 -0.0564 0.1062 0.9929
6.750 1.2378 0.01337 0.00725 -0.0659 0.1042 0.9997
7.000 1.2615 0.01364 0.00754 -0.0654 0.1023 1.0000
7.250 1.2792 0.01392 0.00783 -0.0636 0.1003 1.0000
7.500 1.2959 0.01425 0.00816 -0.0617 0.0980 1.0000
7.750 1.3105 0.01466 0.00856 -0.0594 0.0946 1.0000
8.000 1.3265 0.01497 0.00890 -0.0573 0.0924 1.0000
8.250 1.3425 0.01515 0.00911 -0.0552 0.0909 1.0000
8.500 1.3566 0.01536 0.00933 -0.0528 0.0884 1.0000
8.750 1.3695 0.01564 0.00961 -0.0501 0.0856 1.0000
9.000 1.3810 0.01606 0.01000 -0.0474 0.0813 1.0000
9.250 1.3968 0.01631 0.01028 -0.0455 0.0793 1.0000
9.500 1.4119 0.01663 0.01060 -0.0435 0.0764 1.0000
9.750 1.4261 0.01704 0.01099 -0.0414 0.0734 1.0000
10.000 1.4398 0.01750 0.01146 -0.0394 0.0702 1.0000
10.250 1.4547 0.01791 0.01189 -0.0376 0.0685 1.0000
10.500 1.4691 0.01838 0.01236 -0.0358 0.0660 1.0000
10.750 1.4828 0.01893 0.01289 -0.0340 0.0634 1.0000
11.000 1.4954 0.01957 0.01355 -0.0321 0.0613 1.0000
11.250 1.5104 0.02006 0.01409 -0.0306 0.0605 1.0000
11.500 1.5247 0.02061 0.01468 -0.0291 0.0593 1.0000
11.750 1.5384 0.02123 0.01533 -0.0276 0.0578 1.0000
12.000 1.5513 0.02192 0.01604 -0.0261 0.0563 1.0000
12.250 1.5621 0.02278 0.01690 -0.0244 0.0538 1.0000
12.500 1.5751 0.02350 0.01767 -0.0231 0.0527 1.0000
12.750 1.5890 0.02417 0.01840 -0.0219 0.0519 1.0000
13.000 1.6019 0.02493 0.01920 -0.0206 0.0508 1.0000
13.250 1.6139 0.02576 0.02008 -0.0194 0.0494 1.0000
13.500 1.6241 0.02676 0.02109 -0.0181 0.0476 1.0000
13.750 1.6321 0.02795 0.02231 -0.0167 0.0459 1.0000
14.000 1.6455 0.02875 0.02317 -0.0158 0.0450 1.0000
14.250 1.6572 0.02969 0.02416 -0.0149 0.0429 1.0000
14.500 1.6656 0.03093 0.02541 -0.0139 0.0407 1.0000
14.750 1.6745 0.03216 0.02668 -0.0129 0.0380 1.0000
15.000 1.6801 0.03370 0.02822 -0.0119 0.0342 1.0000
15.250 1.6816 0.03566 0.03017 -0.0108 0.0281 1.0000
15.500 1.6763 0.03831 0.03280 -0.0097 0.0220 1.0000
15.750 1.6728 0.04094 0.03546 -0.0089 0.0195 1.0000
16.000 1.6683 0.04378 0.03836 -0.0083 0.0179 1.0000
16.250 1.6653 0.04654 0.04122 -0.0079 0.0169 1.0000
16.500 1.6603 0.04963 0.04439 -0.0077 0.0161 1.0000
16.750 1.6552 0.05281 0.04766 -0.0076 0.0157 1.0000
17.000 1.6438 0.05680 0.05175 -0.0077 0.0150 1.0000
17.250 1.6343 0.06069 0.05575 -0.0080 0.0147 1.0000
17.500 1.6255 0.06461 0.05978 -0.0084 0.0144 1.0000
17.750 1.6136 0.06903 0.06433 -0.0092 0.0143 1.0000
18.000 1.5984 0.07412 0.06955 -0.0102 0.0140 1.0000
18.250 1.5777 0.08032 0.07590 -0.0119 0.0139 1.0000
18.500 1.5550 0.08743 0.08320 -0.0143 0.0139 1.0000
18.750 1.4963 0.10260 0.09864 -0.0214 0.0142 1.0000
19.000 1.4499 0.11400 0.11018 -0.0265 0.0145 1.0000
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