GOE 425 AIRFOIL (goe425-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 425 AIRFOIL (goe425-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.43 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe425-il-1000000-n5.txt Download as CSV file: xf-goe425-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 425 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.7593 0.06150 0.05850 -0.0668 0.7625 0.0202
-14.000 -0.8190 0.04715 0.04378 -0.0800 0.7536 0.0202
-13.750 -0.8375 0.04061 0.03697 -0.0865 0.7416 0.0203
-13.500 -0.8467 0.03614 0.03226 -0.0907 0.7302 0.0205
-13.250 -0.8508 0.03322 0.02913 -0.0920 0.7215 0.0206
-13.000 -0.8507 0.03125 0.02697 -0.0912 0.7134 0.0207
-12.750 -0.8433 0.02954 0.02508 -0.0905 0.7072 0.0209
-12.500 -0.8316 0.02801 0.02337 -0.0900 0.7011 0.0210
-12.250 -0.8172 0.02666 0.02186 -0.0894 0.6951 0.0212
-12.000 -0.7999 0.02554 0.02059 -0.0889 0.6901 0.0214
-11.750 -0.7807 0.02460 0.01952 -0.0884 0.6845 0.0215
-11.500 -0.7606 0.02373 0.01851 -0.0880 0.6785 0.0216
-11.250 -0.7398 0.02286 0.01751 -0.0876 0.6732 0.0217
-11.000 -0.7180 0.02207 0.01660 -0.0872 0.6673 0.0218
-10.750 -0.6976 0.02101 0.01540 -0.0867 0.6613 0.0220
-10.500 -0.6762 0.02003 0.01431 -0.0862 0.6563 0.0221
-10.250 -0.6529 0.01932 0.01353 -0.0859 0.6510 0.0223
-10.000 -0.6289 0.01874 0.01287 -0.0856 0.6450 0.0224
-9.750 -0.6043 0.01823 0.01229 -0.0853 0.6396 0.0226
-9.500 -0.5792 0.01773 0.01174 -0.0851 0.6339 0.0227
-9.250 -0.5540 0.01728 0.01121 -0.0849 0.6274 0.0228
-9.000 -0.5285 0.01684 0.01071 -0.0846 0.6212 0.0230
-8.750 -0.5029 0.01641 0.01020 -0.0844 0.6139 0.0231
-8.500 -0.4770 0.01604 0.00976 -0.0842 0.6066 0.0233
-8.250 -0.4508 0.01567 0.00933 -0.0841 0.6000 0.0236
-8.000 -0.4247 0.01529 0.00888 -0.0839 0.5930 0.0238
-7.750 -0.3985 0.01490 0.00842 -0.0837 0.5869 0.0240
-7.500 -0.3723 0.01450 0.00795 -0.0835 0.5804 0.0242
-7.250 -0.3461 0.01413 0.00751 -0.0832 0.5740 0.0244
-7.000 -0.3195 0.01377 0.00710 -0.0831 0.5686 0.0246
-6.750 -0.2929 0.01344 0.00670 -0.0829 0.5626 0.0248
-6.500 -0.2663 0.01314 0.00633 -0.0827 0.5566 0.0249
-6.250 -0.2394 0.01284 0.00599 -0.0826 0.5516 0.0251
-6.000 -0.2123 0.01256 0.00566 -0.0824 0.5464 0.0253
-5.750 -0.1853 0.01232 0.00536 -0.0823 0.5417 0.0254
-5.500 -0.1580 0.01208 0.00509 -0.0822 0.5377 0.0255
-5.250 -0.1305 0.01186 0.00483 -0.0821 0.5342 0.0257
-5.000 -0.1038 0.01151 0.00445 -0.0819 0.5303 0.0259
-4.750 -0.0769 0.01124 0.00414 -0.0818 0.5262 0.0263
-4.250 -0.0217 0.01086 0.00371 -0.0816 0.5192 0.0269
-4.000 0.0063 0.01070 0.00355 -0.0816 0.5164 0.0273
-3.750 0.0343 0.01056 0.00339 -0.0816 0.5134 0.0277
-3.500 0.0622 0.01042 0.00322 -0.0816 0.5102 0.0281
-3.250 0.0901 0.01030 0.00307 -0.0816 0.5068 0.0284
-3.000 0.1181 0.01019 0.00293 -0.0816 0.5039 0.0288
-2.750 0.1465 0.01006 0.00280 -0.0816 0.5017 0.0292
-2.500 0.1748 0.00995 0.00267 -0.0817 0.4993 0.0295
-2.250 0.2031 0.00986 0.00257 -0.0817 0.4965 0.0298
-2.000 0.2313 0.00976 0.00245 -0.0818 0.4936 0.0302
-1.750 0.2593 0.00966 0.00234 -0.0818 0.4908 0.0310
-1.500 0.2875 0.00960 0.00226 -0.0818 0.4878 0.0317
-1.250 0.3160 0.00953 0.00219 -0.0819 0.4857 0.0325
-1.000 0.3446 0.00946 0.00213 -0.0820 0.4833 0.0334
-0.750 0.3731 0.00941 0.00209 -0.0821 0.4806 0.0344
-0.500 0.4015 0.00937 0.00204 -0.0822 0.4776 0.0361
-0.250 0.4299 0.00934 0.00201 -0.0823 0.4748 0.0383
0.000 0.4581 0.00932 0.00198 -0.0823 0.4720 0.0414
0.500 0.5145 0.00912 0.00195 -0.0825 0.4676 0.1005
0.750 0.5431 0.00909 0.00195 -0.0827 0.4652 0.1088
1.000 0.5716 0.00908 0.00196 -0.0828 0.4629 0.1167
1.250 0.5998 0.00904 0.00197 -0.0829 0.4603 0.1318
1.500 0.6253 0.00854 0.00196 -0.0828 0.4576 0.3189
1.750 0.6519 0.00832 0.00201 -0.0827 0.4547 0.4208
2.000 0.6798 0.00824 0.00208 -0.0828 0.4526 0.4722
2.250 0.7080 0.00820 0.00214 -0.0829 0.4506 0.5069
2.500 0.7359 0.00816 0.00221 -0.0830 0.4480 0.5438
2.750 0.7639 0.00816 0.00227 -0.0831 0.4445 0.5676
3.000 0.7917 0.00820 0.00234 -0.0832 0.4404 0.5841
3.250 0.8195 0.00824 0.00242 -0.0832 0.4370 0.6030
3.500 0.8477 0.00824 0.00249 -0.0833 0.4342 0.6237
3.750 0.8756 0.00825 0.00257 -0.0834 0.4311 0.6476
4.000 0.9030 0.00826 0.00265 -0.0834 0.4270 0.6768
4.250 0.9294 0.00828 0.00276 -0.0833 0.4220 0.7159
4.500 0.9549 0.00814 0.00286 -0.0828 0.4183 0.7932
4.750 1.0024 0.00793 0.00304 -0.0870 0.4139 0.9901
5.000 1.0383 0.00809 0.00316 -0.0890 0.4074 1.0000
5.250 1.0642 0.00820 0.00326 -0.0887 0.4018 1.0000
5.500 1.0898 0.00832 0.00337 -0.0883 0.3958 1.0000
5.750 1.1148 0.00849 0.00351 -0.0879 0.3897 1.0000
6.000 1.1405 0.00862 0.00363 -0.0876 0.3830 1.0000
6.250 1.1652 0.00882 0.00379 -0.0872 0.3754 1.0000
6.500 1.1905 0.00899 0.00395 -0.0868 0.3673 1.0000
6.750 1.2147 0.00922 0.00413 -0.0863 0.3588 1.0000
7.000 1.2397 0.00941 0.00431 -0.0860 0.3507 1.0000
7.250 1.2637 0.00965 0.00453 -0.0855 0.3430 1.0000
7.500 1.2885 0.00986 0.00472 -0.0851 0.3354 1.0000
7.750 1.3117 0.01015 0.00497 -0.0845 0.3256 1.0000
8.000 1.3339 0.01050 0.00527 -0.0838 0.3130 1.0000
8.250 1.3572 0.01077 0.00553 -0.0832 0.3033 1.0000
8.500 1.3792 0.01112 0.00583 -0.0825 0.2927 1.0000
8.750 1.3987 0.01159 0.00623 -0.0814 0.2751 1.0000
9.000 1.4132 0.01233 0.00681 -0.0795 0.2469 1.0000
9.250 1.4125 0.01374 0.00789 -0.0754 0.1923 1.0000
9.500 1.4138 0.01486 0.00885 -0.0715 0.1645 1.0000
9.750 1.4245 0.01562 0.00957 -0.0693 0.1534 1.0000
10.000 1.4385 0.01628 0.01022 -0.0677 0.1463 1.0000
10.250 1.4499 0.01711 0.01104 -0.0660 0.1386 1.0000
10.500 1.4626 0.01794 0.01187 -0.0645 0.1311 1.0000
10.750 1.4711 0.01909 0.01300 -0.0629 0.1215 1.0000
11.000 1.4802 0.02032 0.01420 -0.0615 0.1118 1.0000
11.250 1.4863 0.02187 0.01573 -0.0602 0.1006 1.0000
11.500 1.4913 0.02363 0.01746 -0.0590 0.0913 1.0000
11.750 1.4968 0.02547 0.01929 -0.0581 0.0846 1.0000
12.000 1.5033 0.02727 0.02112 -0.0573 0.0801 1.0000
12.250 1.5074 0.02932 0.02318 -0.0565 0.0755 1.0000
12.500 1.5145 0.03112 0.02502 -0.0559 0.0726 1.0000
12.750 1.5194 0.03311 0.02705 -0.0552 0.0699 1.0000
13.000 1.5218 0.03534 0.02931 -0.0544 0.0672 1.0000
13.250 1.5258 0.03743 0.03145 -0.0537 0.0648 1.0000
13.500 1.5285 0.03966 0.03372 -0.0530 0.0617 1.0000
13.750 1.5259 0.04241 0.03648 -0.0522 0.0576 1.0000
14.000 1.5274 0.04485 0.03897 -0.0517 0.0544 1.0000
14.250 1.5251 0.04772 0.04186 -0.0511 0.0503 1.0000
14.500 1.5234 0.05060 0.04476 -0.0506 0.0462 1.0000
14.750 1.5196 0.05377 0.04794 -0.0502 0.0415 1.0000
15.000 1.5147 0.05709 0.05127 -0.0498 0.0364 1.0000
15.250 1.5082 0.06061 0.05480 -0.0495 0.0306 1.0000
15.500 1.5007 0.06431 0.05851 -0.0492 0.0248 1.0000
15.750 1.4934 0.06807 0.06229 -0.0491 0.0204 1.0000
16.000 1.4892 0.07145 0.06570 -0.0490 0.0178 1.0000
16.250 1.4865 0.07473 0.06902 -0.0489 0.0162 1.0000
16.500 1.4853 0.07786 0.07220 -0.0490 0.0151 1.0000
16.750 1.4840 0.08102 0.07541 -0.0491 0.0142 1.0000
17.000 1.4829 0.08416 0.07860 -0.0492 0.0135 1.0000
17.250 1.4831 0.08717 0.08166 -0.0494 0.0129 1.0000
17.500 1.4832 0.09021 0.08476 -0.0496 0.0124 1.0000
17.750 1.4822 0.09344 0.08805 -0.0499 0.0120 1.0000
18.000 1.4817 0.09658 0.09123 -0.0503 0.0116 1.0000
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