Eiffel 428 (Bleriot) (eiffel428-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eiffel 428 (Bleriot) (eiffel428-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.45 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eiffel428-il-1000000.txt Download as CSV file: xf-eiffel428-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Eiffel 428 (Bleriot)
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2861 0.10905 0.10750 -0.0335 1.0000 0.0167
-11.750 -0.2859 0.10527 0.10373 -0.0345 1.0000 0.0167
-11.500 -0.2854 0.10144 0.09990 -0.0353 1.0000 0.0168
-11.250 -0.2854 0.09752 0.09599 -0.0361 1.0000 0.0168
-11.000 -0.2846 0.09342 0.09191 -0.0371 0.9998 0.0168
-10.750 -0.2720 0.08948 0.08796 -0.0389 0.9778 0.0175
-10.500 -0.2222 0.08210 0.08049 -0.0525 0.9414 0.0183
-10.250 -0.1950 0.07359 0.07178 -0.0655 0.9007 0.0209
-10.000 -0.1948 0.06975 0.06771 -0.0668 0.8460 0.0210
-9.750 -0.3592 0.08568 0.08411 -0.0384 0.9899 0.0164
-9.500 -0.2850 0.07862 0.07693 -0.0601 0.9356 0.0209
-8.750 -0.2474 0.06407 0.06172 -0.0787 0.7890 0.0189
-8.500 -0.2493 0.05938 0.05697 -0.0824 0.7732 0.0192
-8.250 -0.3178 0.02622 0.02296 -0.0985 0.8042 0.0215
-8.000 -0.2987 0.02556 0.02210 -0.0976 0.7770 0.0219
-7.750 -0.2751 0.02596 0.02239 -0.0969 0.7510 0.0222
-7.500 -0.2508 0.02654 0.02289 -0.0964 0.7290 0.0226
-7.250 -0.2264 0.02694 0.02321 -0.0959 0.7077 0.0232
-7.000 -0.2077 0.02481 0.02081 -0.0952 0.6934 0.0243
-6.750 -0.1942 0.02025 0.01567 -0.0937 0.6835 0.0259
-6.500 -0.1778 0.01719 0.01211 -0.0925 0.6712 0.0274
-6.250 -0.1536 0.01691 0.01171 -0.0919 0.6509 0.0280
-6.000 -0.1296 0.01669 0.01132 -0.0913 0.6190 0.0285
-5.750 -0.1073 0.01647 0.01080 -0.0903 0.5583 0.0291
-5.500 -0.0867 0.01625 0.01011 -0.0891 0.4635 0.0298
-5.250 -0.0718 0.01671 0.00966 -0.0870 0.2154 0.0304
-5.000 -0.0488 0.01626 0.00886 -0.0861 0.1278 0.0312
-4.750 -0.0240 0.01540 0.00781 -0.0855 0.1214 0.0317
-4.500 0.0015 0.01477 0.00705 -0.0850 0.1173 0.0322
-4.250 0.0274 0.01433 0.00650 -0.0845 0.1154 0.0327
-4.000 0.0541 0.01422 0.00632 -0.0842 0.1148 0.0332
-3.750 0.0783 0.01302 0.00499 -0.0835 0.1143 0.0342
-3.500 0.1037 0.01247 0.00440 -0.0830 0.1139 0.0350
-3.250 0.1296 0.01217 0.00407 -0.0826 0.1135 0.0356
-3.000 0.1556 0.01193 0.00380 -0.0822 0.1131 0.0362
-2.750 0.1816 0.01173 0.00358 -0.0818 0.1127 0.0369
-2.500 0.2076 0.01154 0.00337 -0.0814 0.1125 0.0376
-2.250 0.2337 0.01139 0.00320 -0.0809 0.1121 0.0387
-2.000 0.2599 0.01130 0.00309 -0.0806 0.1118 0.0399
-1.750 0.2862 0.01124 0.00301 -0.0802 0.1116 0.0411
-1.500 0.3125 0.01119 0.00294 -0.0798 0.1114 0.0417
-1.250 0.3386 0.01112 0.00286 -0.0794 0.1112 0.0423
-1.000 0.3635 0.01085 0.00254 -0.0788 0.1109 0.0446
-0.750 0.3894 0.01080 0.00249 -0.0784 0.1099 0.0469
-0.500 0.4153 0.01082 0.00250 -0.0780 0.1088 0.0492
-0.250 0.4413 0.01086 0.00253 -0.0776 0.1077 0.0516
0.000 0.4671 0.01094 0.00261 -0.0772 0.1062 0.0532
0.250 0.4925 0.01095 0.00261 -0.0767 0.1054 0.0595
0.500 0.5179 0.01103 0.00271 -0.0763 0.1045 0.0651
0.750 0.5419 0.01081 0.00282 -0.0756 0.1035 0.2025
1.000 0.5627 0.01013 0.00292 -0.0746 0.1028 0.5127
1.250 0.6446 0.00919 0.00310 -0.0872 0.1003 1.0000
1.500 0.6698 0.00930 0.00317 -0.0867 0.0985 1.0000
1.750 0.6949 0.00942 0.00324 -0.0862 0.0959 1.0000
2.000 0.7189 0.00963 0.00342 -0.0855 0.0922 1.0000
2.250 0.7470 0.00949 0.00320 -0.0855 0.0877 1.0000
2.500 0.7704 0.00974 0.00324 -0.0848 0.0512 1.0000
2.750 0.7943 0.00996 0.00346 -0.0840 0.0459 1.0000
3.000 0.8185 0.01016 0.00367 -0.0833 0.0445 1.0000
3.250 0.8424 0.01037 0.00390 -0.0826 0.0426 1.0000
3.500 0.8658 0.01063 0.00416 -0.0818 0.0403 1.0000
3.750 0.8882 0.01097 0.00452 -0.0808 0.0380 1.0000
4.000 0.9105 0.01130 0.00488 -0.0798 0.0366 1.0000
4.250 0.9341 0.01152 0.00510 -0.0791 0.0356 1.0000
4.500 0.9571 0.01178 0.00538 -0.0783 0.0343 1.0000
4.750 0.9798 0.01207 0.00568 -0.0774 0.0326 1.0000
5.000 1.0019 0.01238 0.00600 -0.0764 0.0310 1.0000
5.250 1.0195 0.01303 0.00668 -0.0747 0.0289 1.0000
5.500 1.0416 0.01333 0.00701 -0.0737 0.0280 1.0000
5.750 1.0645 0.01355 0.00724 -0.0730 0.0268 1.0000
6.000 1.0873 0.01378 0.00748 -0.0722 0.0253 1.0000
6.250 1.1091 0.01407 0.00777 -0.0713 0.0240 1.0000
6.500 1.1239 0.01483 0.00856 -0.0692 0.0220 1.0000
6.750 1.1460 0.01507 0.00882 -0.0683 0.0213 1.0000
7.000 1.1681 0.01531 0.00907 -0.0675 0.0202 1.0000
7.250 1.1894 0.01557 0.00934 -0.0665 0.0190 1.0000
7.500 1.2097 0.01590 0.00965 -0.0654 0.0180 1.0000
7.750 1.2205 0.01678 0.01059 -0.0627 0.0167 1.0000
8.000 1.2388 0.01714 0.01100 -0.0613 0.0162 1.0000
8.250 1.2538 0.01758 0.01147 -0.0592 0.0155 1.0000
8.500 1.2702 0.01792 0.01183 -0.0575 0.0148 1.0000
8.750 1.2863 0.01831 0.01222 -0.0558 0.0140 1.0000
9.000 1.2987 0.01892 0.01286 -0.0536 0.0134 1.0000
9.250 1.2988 0.02029 0.01433 -0.0497 0.0127 1.0000
9.500 1.3143 0.02082 0.01491 -0.0483 0.0123 1.0000
9.750 1.3259 0.02163 0.01579 -0.0464 0.0120 1.0000
10.000 1.3383 0.02243 0.01664 -0.0448 0.0116 1.0000
10.250 1.3502 0.02331 0.01758 -0.0433 0.0111 1.0000
10.500 1.3596 0.02443 0.01876 -0.0417 0.0108 1.0000
10.750 1.3701 0.02550 0.01988 -0.0404 0.0105 1.0000
11.000 1.3794 0.02673 0.02115 -0.0391 0.0101 1.0000
11.250 1.3798 0.02877 0.02329 -0.0372 0.0097 1.0000
11.500 1.3763 0.03128 0.02594 -0.0351 0.0094 1.0000
11.750 1.3861 0.03264 0.02736 -0.0343 0.0093 1.0000
12.000 1.3982 0.03381 0.02860 -0.0337 0.0090 1.0000
12.250 1.4048 0.03552 0.03040 -0.0328 0.0088 1.0000
12.500 1.4094 0.03745 0.03243 -0.0319 0.0087 1.0000
12.750 1.4168 0.03915 0.03420 -0.0312 0.0083 1.0000
13.000 1.4192 0.04136 0.03651 -0.0304 0.0082 1.0000
13.250 1.4252 0.04323 0.03846 -0.0299 0.0080 1.0000
13.500 1.4296 0.04531 0.04060 -0.0295 0.0078 1.0000
13.750 1.4338 0.04744 0.04280 -0.0292 0.0076 1.0000
14.000 1.4339 0.05004 0.04549 -0.0287 0.0075 1.0000
14.250 1.4332 0.05280 0.04834 -0.0284 0.0074 1.0000
14.500 1.4276 0.05621 0.05186 -0.0281 0.0072 1.0000
14.750 1.4241 0.05944 0.05521 -0.0279 0.0072 1.0000
15.000 1.3971 0.06560 0.06163 -0.0273 0.0069 1.0000
15.250 1.3866 0.07003 0.06622 -0.0275 0.0069 1.0000
15.500 1.3851 0.07345 0.06976 -0.0282 0.0069 1.0000
15.750 1.3831 0.07705 0.07347 -0.0292 0.0068 1.0000
16.000 1.3740 0.08173 0.07829 -0.0302 0.0067 1.0000
16.250 1.3657 0.08645 0.08314 -0.0315 0.0067 1.0000
16.500 1.3501 0.09239 0.08925 -0.0333 0.0067 1.0000
16.750 1.3409 0.09758 0.09457 -0.0351 0.0066 1.0000
17.000 1.3199 0.10491 0.10207 -0.0378 0.0067 1.0000
17.250 1.3014 0.11214 0.10947 -0.0409 0.0066 1.0000
17.500 1.2919 0.11795 0.11539 -0.0437 0.0066 1.0000
17.750 1.2713 0.12625 0.12385 -0.0478 0.0065 1.0000
18.000 1.2411 0.13710 0.13490 -0.0535 0.0066 1.0000
18.250 1.2039 0.15068 0.14869 -0.0612 0.0067 1.0000
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