GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 476 AIRFOIL (goe476-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.85 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe476-il-1000000.txt Download as CSV file: xf-goe476-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 476 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.3254 0.16207 0.16016 -0.0377 1.0000 0.0289
-15.500 -0.3186 0.15982 0.15793 -0.0382 1.0000 0.0296
-15.000 -0.9880 0.03469 0.03173 -0.1131 0.9991 0.0373
-14.750 -0.9708 0.03260 0.02954 -0.1160 0.9964 0.0376
-14.500 -0.9539 0.03059 0.02740 -0.1182 0.9930 0.0379
-14.250 -0.9413 0.02893 0.02561 -0.1185 0.9879 0.0382
-14.000 -0.9181 0.02746 0.02403 -0.1199 0.9844 0.0385
-13.750 -0.8937 0.02593 0.02236 -0.1215 0.9819 0.0389
-13.500 -0.8709 0.02481 0.02113 -0.1220 0.9783 0.0392
-13.250 -0.8480 0.02394 0.02015 -0.1222 0.9733 0.0396
-13.000 -0.8203 0.02310 0.01920 -0.1231 0.9701 0.0399
-12.750 -0.7944 0.02154 0.01748 -0.1245 0.9674 0.0403
-12.500 -0.7749 0.02037 0.01623 -0.1240 0.9594 0.0408
-12.250 -0.7411 0.01960 0.01541 -0.1259 0.9553 0.0412
-12.000 -0.7072 0.01900 0.01478 -0.1277 0.9500 0.0416
-11.750 -0.6766 0.01844 0.01416 -0.1287 0.9408 0.0420
-11.500 -0.6453 0.01788 0.01352 -0.1298 0.9312 0.0425
-11.250 -0.6151 0.01735 0.01289 -0.1306 0.9192 0.0430
-11.000 -0.5907 0.01686 0.01227 -0.1301 0.9037 0.0434
-10.750 -0.5676 0.01644 0.01173 -0.1294 0.8878 0.0439
-10.500 -0.5444 0.01618 0.01135 -0.1284 0.8724 0.0443
-10.250 -0.5225 0.01587 0.01091 -0.1273 0.8578 0.0446
-10.000 -0.5023 0.01541 0.01031 -0.1259 0.8437 0.0450
-9.750 -0.4844 0.01469 0.00947 -0.1242 0.8303 0.0456
-9.500 -0.4628 0.01432 0.00904 -0.1230 0.8191 0.0461
-9.250 -0.4404 0.01407 0.00872 -0.1219 0.8080 0.0466
-9.000 -0.4173 0.01381 0.00841 -0.1209 0.7973 0.0470
-8.750 -0.3943 0.01357 0.00808 -0.1198 0.7868 0.0475
-8.500 -0.3711 0.01332 0.00776 -0.1188 0.7755 0.0481
-8.250 -0.3475 0.01309 0.00745 -0.1178 0.7650 0.0487
-8.000 -0.3239 0.01291 0.00717 -0.1168 0.7536 0.0493
-7.750 -0.2996 0.01273 0.00691 -0.1159 0.7417 0.0497
-7.500 -0.2758 0.01258 0.00666 -0.1149 0.7289 0.0501
-7.250 -0.2552 0.01201 0.00600 -0.1135 0.7165 0.0510
-7.000 -0.2312 0.01176 0.00571 -0.1126 0.7058 0.0517
-6.500 -0.1820 0.01141 0.00527 -0.1110 0.6877 0.0530
-6.250 -0.1573 0.01127 0.00506 -0.1102 0.6793 0.0538
-6.000 -0.1318 0.01110 0.00485 -0.1095 0.6727 0.0545
-5.750 -0.1059 0.01099 0.00468 -0.1089 0.6662 0.0552
-5.500 -0.0805 0.01091 0.00453 -0.1082 0.6598 0.0558
-5.250 -0.0566 0.01051 0.00412 -0.1073 0.6546 0.0570
-5.000 -0.0310 0.01033 0.00392 -0.1067 0.6492 0.0580
-4.750 -0.0055 0.01022 0.00377 -0.1061 0.6439 0.0589
-4.500 0.0202 0.01012 0.00363 -0.1054 0.6389 0.0600
-4.250 0.0469 0.00998 0.00349 -0.1050 0.6353 0.0609
-4.000 0.0734 0.00989 0.00337 -0.1045 0.6310 0.0618
-3.750 0.0986 0.00969 0.00314 -0.1038 0.6268 0.0633
-3.500 0.1239 0.00958 0.00301 -0.1031 0.6222 0.0648
-3.250 0.1504 0.00948 0.00290 -0.1026 0.6186 0.0662
-3.000 0.1772 0.00937 0.00280 -0.1022 0.6149 0.0677
-2.750 0.2038 0.00931 0.00271 -0.1017 0.6108 0.0689
-2.500 0.2290 0.00916 0.00255 -0.1010 0.6068 0.0714
-2.250 0.2548 0.00912 0.00249 -0.1004 0.6022 0.0738
-2.000 0.2817 0.00903 0.00241 -0.1000 0.5994 0.0761
-1.750 0.3080 0.00890 0.00231 -0.0995 0.5960 0.0796
-1.500 0.3342 0.00882 0.00225 -0.0990 0.5922 0.0836
-1.250 0.3599 0.00875 0.00218 -0.0983 0.5882 0.0890
-1.000 0.3853 0.00872 0.00215 -0.0977 0.5837 0.0972
-0.750 0.4117 0.00862 0.00214 -0.0972 0.5806 0.1104
-0.500 0.4381 0.00855 0.00213 -0.0967 0.5761 0.1233
-0.250 0.4638 0.00854 0.00212 -0.0961 0.5704 0.1322
0.000 0.4890 0.00857 0.00215 -0.0954 0.5649 0.1401
0.250 0.5160 0.00854 0.00214 -0.0950 0.5609 0.1453
0.500 0.5420 0.00851 0.00214 -0.0945 0.5562 0.1527
0.750 0.5676 0.00853 0.00215 -0.0939 0.5512 0.1576
1.000 0.5927 0.00855 0.00215 -0.0931 0.5455 0.1621
1.250 0.6187 0.00851 0.00215 -0.0926 0.5400 0.1686
1.500 0.6439 0.00852 0.00216 -0.0919 0.5342 0.1739
1.750 0.6682 0.00856 0.00218 -0.0910 0.5285 0.1797
2.000 0.6940 0.00852 0.00220 -0.0905 0.5235 0.1884
2.750 0.7659 0.00847 0.00232 -0.0877 0.5051 0.2601
3.000 0.7821 0.00808 0.00243 -0.0854 0.4977 0.4622
3.250 0.8791 0.00741 0.00301 -0.1006 0.4879 0.9801
3.500 0.9351 0.00767 0.00319 -0.1066 0.4797 0.9881
3.750 0.9782 0.00786 0.00335 -0.1099 0.4724 0.9931
4.000 1.0285 0.00801 0.00343 -0.1148 0.4631 0.9969
4.250 1.0717 0.00816 0.00352 -0.1182 0.4526 0.9995
4.750 1.1173 0.00843 0.00371 -0.1161 0.4361 1.0000
5.000 1.1368 0.00858 0.00383 -0.1144 0.4292 1.0000
5.250 1.1557 0.00873 0.00395 -0.1125 0.4228 1.0000
5.500 1.1757 0.00885 0.00406 -0.1109 0.4157 1.0000
6.000 1.2120 0.00917 0.00433 -0.1069 0.4005 1.0000
6.250 1.2289 0.00935 0.00448 -0.1047 0.3929 1.0000
6.500 1.2463 0.00951 0.00463 -0.1025 0.3858 1.0000
6.750 1.2625 0.00968 0.00478 -0.1002 0.3769 1.0000
7.000 1.2760 0.00987 0.00494 -0.0973 0.3675 1.0000
7.250 1.2840 0.01010 0.00512 -0.0932 0.3555 1.0000
7.500 1.2927 0.01037 0.00533 -0.0894 0.3390 1.0000
7.750 1.2979 0.01079 0.00562 -0.0851 0.3121 1.0000
8.000 1.2945 0.01153 0.00614 -0.0793 0.2744 1.0000
8.250 1.2957 0.01224 0.00670 -0.0746 0.2475 1.0000
8.500 1.3038 0.01281 0.00719 -0.0712 0.2328 1.0000
8.750 1.3143 0.01332 0.00766 -0.0684 0.2226 1.0000
9.000 1.3265 0.01382 0.00813 -0.0659 0.2148 1.0000
9.250 1.3394 0.01432 0.00861 -0.0636 0.2080 1.0000
9.500 1.3541 0.01476 0.00906 -0.0617 0.2028 1.0000
9.750 1.3668 0.01533 0.00962 -0.0595 0.1971 1.0000
10.000 1.3807 0.01587 0.01016 -0.0576 0.1922 1.0000
10.250 1.3960 0.01638 0.01068 -0.0560 0.1873 1.0000
10.500 1.4081 0.01706 0.01135 -0.0540 0.1814 1.0000
10.750 1.4215 0.01772 0.01201 -0.0523 0.1762 1.0000
11.000 1.4356 0.01837 0.01267 -0.0508 0.1708 1.0000
11.250 1.4459 0.01925 0.01353 -0.0489 0.1642 1.0000
11.500 1.4594 0.02000 0.01430 -0.0474 0.1592 1.0000
11.750 1.4700 0.02094 0.01523 -0.0458 0.1526 1.0000
12.000 1.4803 0.02194 0.01623 -0.0442 0.1459 1.0000
12.250 1.4883 0.02313 0.01739 -0.0425 0.1383 1.0000
12.500 1.4963 0.02437 0.01862 -0.0409 0.1307 1.0000
12.750 1.5015 0.02585 0.02008 -0.0392 0.1230 1.0000
13.000 1.5059 0.02743 0.02163 -0.0376 0.1143 1.0000
13.250 1.5083 0.02923 0.02341 -0.0359 0.1046 1.0000
13.500 1.5093 0.03121 0.02536 -0.0343 0.0948 1.0000
13.750 1.5059 0.03360 0.02769 -0.0326 0.0828 1.0000
14.000 1.5030 0.03606 0.03010 -0.0312 0.0733 1.0000
14.250 1.5043 0.03821 0.03226 -0.0300 0.0684 1.0000
14.500 1.5053 0.04044 0.03449 -0.0289 0.0647 1.0000
14.750 1.5091 0.04248 0.03657 -0.0281 0.0629 1.0000
15.000 1.5116 0.04466 0.03878 -0.0273 0.0611 1.0000
15.250 1.5133 0.04695 0.04110 -0.0265 0.0593 1.0000
15.500 1.5145 0.04935 0.04354 -0.0258 0.0580 1.0000
15.750 1.5204 0.05128 0.04553 -0.0253 0.0570 1.0000
16.000 1.5239 0.05350 0.04781 -0.0248 0.0562 1.0000
16.250 1.5273 0.05576 0.05012 -0.0243 0.0554 1.0000
16.500 1.5282 0.05828 0.05269 -0.0239 0.0543 1.0000
16.750 1.5278 0.06100 0.05545 -0.0235 0.0533 1.0000
17.000 1.5265 0.06385 0.05834 -0.0232 0.0522 1.0000
17.250 1.5258 0.06671 0.06127 -0.0230 0.0515 1.0000
17.500 1.5306 0.06894 0.06356 -0.0229 0.0511 1.0000
17.750 1.5327 0.07151 0.06620 -0.0228 0.0506 1.0000
18.000 1.5357 0.07396 0.06872 -0.0228 0.0500 1.0000
18.250 1.5361 0.07680 0.07162 -0.0228 0.0494 1.0000
18.500 1.5380 0.07945 0.07433 -0.0229 0.0488 1.0000
18.750 1.5369 0.08252 0.07745 -0.0231 0.0481 1.0000
19.000 1.5353 0.08562 0.08061 -0.0233 0.0476 1.0000
19.250 1.5318 0.08904 0.08408 -0.0237 0.0469 1.0000
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