Eiffel 430 (Lachassgne) (eiffel430-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eiffel 430 (Lachassgne) (eiffel430-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.84 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eiffel430-il-1000000-n5.txt Download as CSV file: xf-eiffel430-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8512 0.03092 0.02627 -0.1023 0.4914 0.0239
-13.500 -0.8422 0.02791 0.02305 -0.1016 0.4808 0.0241
-13.250 -0.8300 0.02618 0.02093 -0.1002 0.3783 0.0242
-13.000 -0.8142 0.02498 0.01951 -0.0988 0.3057 0.0244
-12.500 -0.7767 0.02295 0.01723 -0.0965 0.2942 0.0247
-12.250 -0.7567 0.02212 0.01628 -0.0953 0.2907 0.0249
-12.000 -0.7364 0.02133 0.01537 -0.0941 0.2876 0.0250
-11.750 -0.7151 0.02064 0.01457 -0.0930 0.2846 0.0252
-11.500 -0.6934 0.01999 0.01383 -0.0919 0.2828 0.0255
-11.250 -0.6710 0.01942 0.01316 -0.0909 0.2808 0.0257
-11.000 -0.6486 0.01885 0.01248 -0.0898 0.2788 0.0259
-10.750 -0.6263 0.01825 0.01177 -0.0887 0.2768 0.0261
-10.500 -0.6036 0.01770 0.01111 -0.0876 0.2748 0.0263
-10.250 -0.5805 0.01718 0.01048 -0.0866 0.2730 0.0265
-10.000 -0.5570 0.01672 0.00992 -0.0856 0.2713 0.0267
-9.750 -0.5331 0.01628 0.00939 -0.0846 0.2702 0.0269
-9.500 -0.5090 0.01586 0.00888 -0.0837 0.2688 0.0271
-9.250 -0.4845 0.01549 0.00842 -0.0828 0.2672 0.0272
-9.000 -0.4597 0.01515 0.00800 -0.0820 0.2657 0.0274
-8.750 -0.4354 0.01474 0.00751 -0.0811 0.2644 0.0276
-8.500 -0.4113 0.01431 0.00700 -0.0801 0.2631 0.0279
-8.250 -0.3863 0.01399 0.00662 -0.0793 0.2618 0.0283
-8.000 -0.3610 0.01372 0.00630 -0.0785 0.2604 0.0286
-7.750 -0.3354 0.01349 0.00602 -0.0778 0.2590 0.0289
-7.500 -0.3096 0.01327 0.00576 -0.0771 0.2580 0.0292
-7.250 -0.2837 0.01306 0.00551 -0.0764 0.2574 0.0295
-7.000 -0.2577 0.01286 0.00527 -0.0757 0.2567 0.0299
-6.750 -0.2315 0.01269 0.00506 -0.0751 0.2559 0.0304
-6.500 -0.2053 0.01251 0.00484 -0.0744 0.2551 0.0308
-6.250 -0.1792 0.01233 0.00462 -0.0738 0.2542 0.0312
-6.000 -0.1529 0.01217 0.00442 -0.0731 0.2533 0.0315
-5.750 -0.1267 0.01202 0.00422 -0.0725 0.2524 0.0318
-5.500 -0.1004 0.01186 0.00403 -0.0719 0.2515 0.0321
-5.250 -0.0744 0.01166 0.00380 -0.0713 0.2506 0.0328
-5.000 -0.0480 0.01153 0.00365 -0.0707 0.2498 0.0334
-4.750 -0.0216 0.01141 0.00352 -0.0701 0.2489 0.0341
-4.500 0.0048 0.01132 0.00341 -0.0695 0.2478 0.0347
-4.250 0.0311 0.01124 0.00330 -0.0689 0.2459 0.0355
-4.000 0.0576 0.01116 0.00319 -0.0684 0.2445 0.0362
-3.750 0.0842 0.01108 0.00309 -0.0679 0.2437 0.0368
-3.500 0.1107 0.01099 0.00300 -0.0673 0.2432 0.0377
-3.250 0.1370 0.01090 0.00291 -0.0667 0.2425 0.0389
-3.000 0.1634 0.01083 0.00285 -0.0662 0.2417 0.0402
-2.750 0.1899 0.01078 0.00279 -0.0657 0.2409 0.0413
-2.500 0.2163 0.01074 0.00274 -0.0651 0.2402 0.0424
-2.250 0.2427 0.01070 0.00270 -0.0646 0.2393 0.0434
-2.000 0.2688 0.01063 0.00263 -0.0640 0.2383 0.0454
-1.750 0.2951 0.01058 0.00258 -0.0635 0.2370 0.0471
-1.500 0.3214 0.01055 0.00254 -0.0630 0.2359 0.0490
-1.250 0.3476 0.01054 0.00252 -0.0624 0.2349 0.0510
-1.000 0.3735 0.01050 0.00249 -0.0619 0.2339 0.0546
-0.500 0.4241 0.01041 0.00251 -0.0605 0.2317 0.0855
-0.250 0.4502 0.01039 0.00253 -0.0600 0.2308 0.0983
0.000 0.4761 0.01038 0.00255 -0.0595 0.2301 0.1059
0.250 0.5021 0.01039 0.00258 -0.0589 0.2293 0.1116
0.500 0.5281 0.01040 0.00262 -0.0584 0.2283 0.1175
1.000 0.5795 0.01042 0.00276 -0.0574 0.2260 0.1509
1.250 0.6055 0.01047 0.00284 -0.0569 0.2247 0.1636
1.500 0.6316 0.01052 0.00289 -0.0564 0.2232 0.1698
1.750 0.6575 0.01057 0.00296 -0.0559 0.2215 0.1740
2.000 0.6833 0.01062 0.00302 -0.0555 0.2198 0.1778
2.250 0.7089 0.01070 0.00309 -0.0549 0.2179 0.1807
2.500 0.7347 0.01076 0.00317 -0.0545 0.2166 0.1840
2.750 0.7603 0.01080 0.00325 -0.0540 0.2139 0.1885
3.000 0.7861 0.01085 0.00330 -0.0535 0.2087 0.1909
3.250 0.8113 0.01091 0.00334 -0.0530 0.2026 0.1925
3.500 0.8344 0.01108 0.00338 -0.0521 0.1768 0.1939
3.750 0.8454 0.01182 0.00385 -0.0491 0.1220 0.1948
4.000 0.8665 0.01206 0.00406 -0.0478 0.1158 0.1958
4.250 0.8881 0.01227 0.00426 -0.0467 0.1108 0.1965
4.500 0.9105 0.01242 0.00443 -0.0456 0.1087 0.1986
4.750 0.9325 0.01258 0.00461 -0.0446 0.1069 0.2006
5.000 0.9542 0.01274 0.00479 -0.0435 0.1054 0.2018
5.250 0.9753 0.01293 0.00500 -0.0422 0.1036 0.2033
5.500 0.9959 0.01313 0.00521 -0.0409 0.1019 0.2045
5.750 1.0162 0.01334 0.00542 -0.0396 0.1001 0.2059
6.000 1.0351 0.01354 0.00564 -0.0380 0.0980 0.2072
6.250 1.0527 0.01374 0.00587 -0.0361 0.0963 0.2088
6.750 1.0904 0.01406 0.00626 -0.0329 0.0945 0.2143
7.000 1.1089 0.01426 0.00650 -0.0312 0.0934 0.2175
7.250 1.1274 0.01447 0.00675 -0.0297 0.0920 0.2202
7.500 1.1453 0.01472 0.00703 -0.0280 0.0901 0.2229
8.000 1.1800 0.01529 0.00763 -0.0246 0.0857 0.2342
8.250 1.1968 0.01558 0.00797 -0.0229 0.0836 0.2571
8.750 1.3589 0.01583 0.00951 -0.0484 0.0668 0.9995
9.000 1.3801 0.01626 0.00991 -0.0477 0.0632 1.0000
9.250 1.3942 0.01661 0.01027 -0.0455 0.0613 1.0000
9.500 1.4081 0.01701 0.01067 -0.0434 0.0590 1.0000
9.750 1.4219 0.01745 0.01112 -0.0413 0.0569 1.0000
10.000 1.4356 0.01793 0.01159 -0.0393 0.0545 1.0000
10.250 1.4505 0.01836 0.01205 -0.0376 0.0533 1.0000
10.500 1.4654 0.01881 0.01253 -0.0359 0.0523 1.0000
10.750 1.4797 0.01931 0.01306 -0.0342 0.0509 1.0000
11.000 1.4936 0.01987 0.01364 -0.0325 0.0494 1.0000
11.250 1.5070 0.02049 0.01426 -0.0309 0.0478 1.0000
11.500 1.5206 0.02111 0.01491 -0.0293 0.0465 1.0000
11.750 1.5348 0.02170 0.01554 -0.0279 0.0457 1.0000
12.000 1.5490 0.02230 0.01620 -0.0265 0.0449 1.0000
12.250 1.5623 0.02299 0.01691 -0.0252 0.0432 1.0000
12.500 1.5747 0.02375 0.01770 -0.0238 0.0417 1.0000
12.750 1.5862 0.02460 0.01857 -0.0224 0.0400 1.0000
13.000 1.5979 0.02545 0.01945 -0.0210 0.0382 1.0000
13.250 1.6090 0.02636 0.02039 -0.0198 0.0357 1.0000
13.500 1.6179 0.02747 0.02150 -0.0184 0.0329 1.0000
13.750 1.6249 0.02874 0.02277 -0.0170 0.0284 1.0000
14.000 1.6195 0.03106 0.02501 -0.0148 0.0183 1.0000
14.250 1.6216 0.03285 0.02685 -0.0134 0.0159 1.0000
14.500 1.6250 0.03461 0.02866 -0.0123 0.0146 1.0000
14.750 1.6277 0.03650 0.03062 -0.0113 0.0135 1.0000
15.000 1.6320 0.03829 0.03248 -0.0106 0.0130 1.0000
15.250 1.6344 0.04034 0.03460 -0.0099 0.0124 1.0000
15.500 1.6352 0.04262 0.03696 -0.0093 0.0119 1.0000
15.750 1.6350 0.04507 0.03948 -0.0089 0.0114 1.0000
16.000 1.6349 0.04758 0.04207 -0.0086 0.0110 1.0000
16.250 1.6356 0.05006 0.04465 -0.0085 0.0108 1.0000
16.500 1.6345 0.05280 0.04747 -0.0084 0.0106 1.0000
16.750 1.6308 0.05587 0.05063 -0.0085 0.0102 1.0000
17.000 1.6259 0.05917 0.05403 -0.0086 0.0100 1.0000
17.250 1.6188 0.06283 0.05779 -0.0090 0.0098 1.0000
17.500 1.6099 0.06681 0.06189 -0.0095 0.0097 1.0000
17.750 1.5973 0.07144 0.06663 -0.0104 0.0095 1.0000
18.000 1.5797 0.07699 0.07231 -0.0117 0.0093 1.0000
18.250 1.5593 0.08332 0.07880 -0.0136 0.0093 1.0000
18.500 1.5358 0.09112 0.08678 -0.0165 0.0093 1.0000
18.750 1.4732 0.10670 0.10263 -0.0239 0.0096 1.0000
19.000 1.4360 0.11648 0.11255 -0.0282 0.0097 1.0000
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Polar data table (+)
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