Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il) Reynolds number: 500,000 Max Cl/Cd: 71.37 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel430-il-500000-n5.txt Download as CSV file: xf-eiffel430-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5339 0.03119 0.02531 -0.0923 0.2929 0.0290
-10.250 -0.5242 0.02807 0.02185 -0.0913 0.2913 0.0293
-10.000 -0.5098 0.02613 0.01965 -0.0900 0.2894 0.0296
-9.750 -0.4934 0.02456 0.01783 -0.0886 0.2876 0.0299
-9.500 -0.4755 0.02324 0.01628 -0.0873 0.2857 0.0302
-9.250 -0.4562 0.02212 0.01494 -0.0860 0.2842 0.0306
-9.000 -0.4356 0.02114 0.01376 -0.0848 0.2827 0.0309
-8.750 -0.4142 0.02029 0.01273 -0.0836 0.2809 0.0312
-8.500 -0.3920 0.01955 0.01182 -0.0825 0.2791 0.0315
-8.250 -0.3690 0.01893 0.01104 -0.0815 0.2775 0.0318
-8.000 -0.3458 0.01834 0.01030 -0.0805 0.2760 0.0320
-7.750 -0.3231 0.01767 0.00953 -0.0794 0.2746 0.0324
-7.500 -0.2992 0.01724 0.00903 -0.0785 0.2732 0.0328
-7.250 -0.2748 0.01693 0.00865 -0.0776 0.2719 0.0332
-7.000 -0.2499 0.01663 0.00830 -0.0768 0.2709 0.0337
-6.750 -0.2249 0.01633 0.00794 -0.0760 0.2700 0.0342
-6.500 -0.1999 0.01599 0.00753 -0.0752 0.2689 0.0347
-6.250 -0.1748 0.01566 0.00713 -0.0744 0.2679 0.0352
-6.000 -0.1497 0.01536 0.00675 -0.0736 0.2668 0.0357
-5.750 -0.1244 0.01508 0.00640 -0.0729 0.2658 0.0363
-5.500 -0.0990 0.01483 0.00608 -0.0721 0.2647 0.0367
-5.250 -0.0734 0.01463 0.00581 -0.0714 0.2638 0.0371
-5.000 -0.0485 0.01430 0.00546 -0.0706 0.2628 0.0379
-4.750 -0.0232 0.01410 0.00523 -0.0699 0.2619 0.0386
-4.500 0.0024 0.01395 0.00506 -0.0692 0.2611 0.0393
-4.250 0.0279 0.01383 0.00490 -0.0684 0.2601 0.0403
-4.000 0.0532 0.01374 0.00477 -0.0677 0.2590 0.0414
-3.750 0.0787 0.01365 0.00465 -0.0670 0.2581 0.0424
-3.500 0.1045 0.01355 0.00452 -0.0663 0.2574 0.0431
-3.250 0.1299 0.01334 0.00432 -0.0656 0.2564 0.0444
-3.000 0.1557 0.01320 0.00418 -0.0650 0.2549 0.0458
-2.750 0.1815 0.01311 0.00407 -0.0643 0.2535 0.0472
-2.500 0.2073 0.01303 0.00398 -0.0637 0.2523 0.0488
-2.250 0.2329 0.01299 0.00392 -0.0630 0.2514 0.0503
-2.000 0.2581 0.01289 0.00382 -0.0623 0.2506 0.0532
-1.750 0.2834 0.01284 0.00377 -0.0616 0.2498 0.0559
-1.500 0.3087 0.01281 0.00373 -0.0608 0.2490 0.0593
-1.250 0.3336 0.01275 0.00371 -0.0601 0.2482 0.0657
-1.000 0.3581 0.01267 0.00375 -0.0593 0.2474 0.0946
-0.750 0.3829 0.01269 0.00378 -0.0585 0.2466 0.1071
-0.500 0.4075 0.01274 0.00384 -0.0577 0.2454 0.1170
-0.250 0.4323 0.01277 0.00390 -0.0570 0.2445 0.1257
0.000 0.4579 0.01277 0.00398 -0.0564 0.2434 0.1393
0.250 0.4836 0.01282 0.00408 -0.0558 0.2420 0.1540
0.500 0.5090 0.01289 0.00418 -0.0552 0.2409 0.1642
0.750 0.5343 0.01298 0.00428 -0.0546 0.2399 0.1720
1.000 0.5596 0.01307 0.00439 -0.0540 0.2389 0.1783
1.250 0.5847 0.01316 0.00446 -0.0533 0.2378 0.1825
1.500 0.6096 0.01322 0.00455 -0.0526 0.2367 0.1865
1.750 0.6346 0.01330 0.00464 -0.0520 0.2356 0.1911
2.000 0.6596 0.01339 0.00473 -0.0514 0.2344 0.1957
2.250 0.6839 0.01345 0.00480 -0.0506 0.2332 0.1988
2.500 0.7078 0.01353 0.00489 -0.0498 0.2320 0.2011
2.750 0.7320 0.01360 0.00499 -0.0491 0.2308 0.2036
3.000 0.7564 0.01367 0.00510 -0.0484 0.2295 0.2063
3.250 0.7806 0.01374 0.00521 -0.0476 0.2279 0.2084
3.500 0.8048 0.01381 0.00531 -0.0469 0.2261 0.2100
3.750 0.8295 0.01383 0.00536 -0.0463 0.2232 0.2115
4.000 0.8546 0.01378 0.00532 -0.0457 0.2193 0.2140
4.250 0.8788 0.01381 0.00540 -0.0450 0.2151 0.2169
4.500 0.9030 0.01385 0.00549 -0.0444 0.2096 0.2191
4.750 0.9272 0.01388 0.00552 -0.0437 0.2032 0.2210
5.000 0.9509 0.01393 0.00555 -0.0429 0.1897 0.2232
5.500 0.9772 0.01492 0.00612 -0.0379 0.1218 0.2288
5.750 0.9932 0.01519 0.00640 -0.0358 0.1179 0.2329
6.000 1.0089 0.01548 0.00671 -0.0336 0.1144 0.2371
6.500 1.0422 0.01605 0.00737 -0.0297 0.1094 0.2537
6.750 1.0525 0.01580 0.00776 -0.0267 0.1080 0.6024
7.750 1.2490 0.01750 0.01033 -0.0483 0.0951 1.0000
8.250 1.2786 0.01815 0.01106 -0.0440 0.0917 1.0000
8.500 1.2933 0.01853 0.01146 -0.0420 0.0895 1.0000
8.750 1.3076 0.01897 0.01192 -0.0400 0.0872 1.0000
9.000 1.3212 0.01948 0.01244 -0.0379 0.0849 1.0000
9.250 1.3361 0.01994 0.01293 -0.0362 0.0827 1.0000
9.500 1.3521 0.02036 0.01339 -0.0346 0.0796 1.0000
9.750 1.3671 0.02086 0.01389 -0.0330 0.0760 1.0000
10.000 1.3813 0.02145 0.01446 -0.0314 0.0729 1.0000
10.250 1.3959 0.02200 0.01505 -0.0298 0.0704 1.0000
10.500 1.4099 0.02261 0.01569 -0.0283 0.0680 1.0000
10.750 1.4234 0.02330 0.01637 -0.0268 0.0652 1.0000
11.000 1.4362 0.02404 0.01712 -0.0253 0.0630 1.0000
11.250 1.4494 0.02474 0.01789 -0.0238 0.0612 1.0000
11.500 1.4619 0.02553 0.01871 -0.0224 0.0594 1.0000
11.750 1.4737 0.02638 0.01960 -0.0210 0.0577 1.0000
12.000 1.4847 0.02732 0.02056 -0.0196 0.0561 1.0000
12.250 1.4950 0.02832 0.02161 -0.0182 0.0549 1.0000
12.500 1.5055 0.02933 0.02268 -0.0170 0.0537 1.0000
12.750 1.5163 0.03033 0.02377 -0.0158 0.0527 1.0000
13.000 1.5267 0.03140 0.02490 -0.0147 0.0512 1.0000
13.250 1.5359 0.03261 0.02616 -0.0136 0.0496 1.0000
13.500 1.5440 0.03392 0.02753 -0.0126 0.0483 1.0000
13.750 1.5508 0.03540 0.02906 -0.0116 0.0470 1.0000
14.000 1.5576 0.03691 0.03064 -0.0108 0.0458 1.0000
14.250 1.5664 0.03828 0.03210 -0.0101 0.0444 1.0000
14.500 1.5732 0.03985 0.03376 -0.0094 0.0430 1.0000
14.750 1.5778 0.04170 0.03564 -0.0088 0.0403 1.0000
15.000 1.5821 0.04362 0.03763 -0.0083 0.0384 1.0000
15.250 1.5865 0.04557 0.03967 -0.0079 0.0361 1.0000
15.500 1.5874 0.04794 0.04207 -0.0076 0.0327 1.0000
15.750 1.5852 0.05071 0.04487 -0.0073 0.0278 1.0000
16.000 1.5769 0.05424 0.04843 -0.0073 0.0225 1.0000
16.250 1.5674 0.05802 0.05227 -0.0073 0.0201 1.0000
16.500 1.5559 0.06218 0.05652 -0.0077 0.0185 1.0000
16.750 1.5414 0.06688 0.06133 -0.0083 0.0172 1.0000
17.000 1.5265 0.07182 0.06640 -0.0092 0.0165 1.0000
17.250 1.5103 0.07724 0.07197 -0.0105 0.0161 1.0000
17.500 1.4899 0.08369 0.07858 -0.0125 0.0160 1.0000
17.750 1.4677 0.09141 0.08650 -0.0155 0.0158 1.0000
18.000 1.4321 0.10220 0.09749 -0.0206 0.0159 1.0000
18.250 1.4031 0.11075 0.10617 -0.0244 0.0160 1.0000
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