GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 621 AIRFOIL (goe621-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.83 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe621-il-1000000-n5.txt Download as CSV file: xf-goe621-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 621 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
------ -------- --------- --------- -------- -------- --------
-17.000 -0.6967 0.09316 0.09066 -0.0755 1.0000 0.0238
-16.750 -0.7411 0.08260 0.07994 -0.0818 1.0000 0.0239
-16.500 -0.7756 0.07418 0.07141 -0.0868 1.0000 0.0240
-16.000 -0.8300 0.05870 0.05569 -0.0984 0.9868 0.0241
-15.750 -0.8454 0.05134 0.04819 -0.1062 0.9805 0.0242
-15.500 -0.8574 0.04392 0.04062 -0.1151 0.9741 0.0243
-15.250 -0.8531 0.03765 0.03420 -0.1245 0.9704 0.0244
-15.000 -0.8386 0.03216 0.02855 -0.1341 0.9655 0.0246
-14.750 -0.8212 0.02705 0.02321 -0.1445 0.9574 0.0247
-14.500 -0.8151 0.02492 0.02094 -0.1463 0.9466 0.0249
-14.250 -0.8137 0.02359 0.01948 -0.1448 0.9372 0.0250
-14.000 -0.8125 0.02264 0.01843 -0.1420 0.9283 0.0251
-13.750 -0.8096 0.02186 0.01755 -0.1389 0.9211 0.0252
-13.500 -0.7996 0.02111 0.01671 -0.1369 0.9141 0.0253
-13.250 -0.7864 0.02042 0.01593 -0.1352 0.9081 0.0254
-13.000 -0.7718 0.01976 0.01520 -0.1336 0.9019 0.0255
-12.750 -0.7553 0.01917 0.01451 -0.1322 0.8957 0.0257
-12.500 -0.7375 0.01860 0.01386 -0.1309 0.8901 0.0258
-12.250 -0.7186 0.01808 0.01326 -0.1297 0.8834 0.0259
-12.000 -0.6987 0.01761 0.01270 -0.1286 0.8762 0.0260
-11.750 -0.6817 0.01688 0.01191 -0.1272 0.8689 0.0263
-11.500 -0.6622 0.01633 0.01127 -0.1260 0.8605 0.0265
-11.250 -0.6414 0.01583 0.01071 -0.1250 0.8530 0.0268
-11.000 -0.6197 0.01540 0.01021 -0.1241 0.8439 0.0270
-10.750 -0.5974 0.01499 0.00974 -0.1232 0.8348 0.0272
-10.500 -0.5749 0.01463 0.00929 -0.1223 0.8236 0.0274
-10.250 -0.5518 0.01428 0.00886 -0.1214 0.8117 0.0276
-10.000 -0.5286 0.01396 0.00846 -0.1206 0.7994 0.0279
-9.750 -0.5053 0.01367 0.00808 -0.1198 0.7872 0.0281
-9.500 -0.4813 0.01337 0.00770 -0.1190 0.7755 0.0284
-9.250 -0.4572 0.01310 0.00736 -0.1183 0.7650 0.0286
-9.000 -0.4330 0.01284 0.00701 -0.1176 0.7547 0.0289
-8.750 -0.4083 0.01258 0.00668 -0.1170 0.7455 0.0291
-8.250 -0.3581 0.01212 0.00608 -0.1158 0.7287 0.0296
-8.000 -0.3326 0.01191 0.00580 -0.1152 0.7213 0.0298
-7.750 -0.3071 0.01168 0.00552 -0.1147 0.7154 0.0301
-7.500 -0.2817 0.01139 0.00519 -0.1142 0.7097 0.0306
-7.250 -0.2559 0.01117 0.00493 -0.1137 0.7038 0.0312
-7.000 -0.2299 0.01098 0.00470 -0.1132 0.6983 0.0317
-6.750 -0.2033 0.01078 0.00448 -0.1128 0.6933 0.0321
-6.500 -0.1768 0.01061 0.00427 -0.1124 0.6881 0.0326
-6.250 -0.1504 0.01046 0.00407 -0.1120 0.6833 0.0331
-6.000 -0.1235 0.01030 0.00388 -0.1117 0.6793 0.0336
-5.750 -0.0964 0.01015 0.00371 -0.1114 0.6749 0.0341
-5.500 -0.0696 0.01001 0.00353 -0.1110 0.6693 0.0347
-5.000 -0.0162 0.00972 0.00319 -0.1103 0.6582 0.0366
-4.750 0.0108 0.00960 0.00305 -0.1100 0.6524 0.0376
-4.500 0.0377 0.00950 0.00292 -0.1096 0.6472 0.0388
-4.250 0.0648 0.00939 0.00279 -0.1093 0.6425 0.0402
-4.000 0.0920 0.00926 0.00267 -0.1090 0.6371 0.0423
-3.750 0.1190 0.00918 0.00256 -0.1087 0.6315 0.0445
-3.500 0.1457 0.00909 0.00245 -0.1083 0.6268 0.0475
-3.250 0.1733 0.00898 0.00236 -0.1081 0.6225 0.0507
-3.000 0.2004 0.00887 0.00226 -0.1077 0.6168 0.0555
-2.750 0.2269 0.00879 0.00217 -0.1073 0.6108 0.0624
-2.500 0.2537 0.00865 0.00209 -0.1070 0.6056 0.0765
-2.250 0.2806 0.00855 0.00204 -0.1067 0.5994 0.0919
-2.000 0.3070 0.00851 0.00199 -0.1062 0.5929 0.1006
-1.750 0.3344 0.00847 0.00195 -0.1060 0.5869 0.1075
-1.500 0.3612 0.00841 0.00191 -0.1056 0.5801 0.1155
-1.250 0.3877 0.00841 0.00188 -0.1052 0.5741 0.1216
-1.000 0.4150 0.00834 0.00185 -0.1050 0.5688 0.1324
-0.750 0.4415 0.00827 0.00183 -0.1046 0.5626 0.1495
-0.500 0.4672 0.00819 0.00181 -0.1041 0.5561 0.1768
-0.250 0.4931 0.00808 0.00181 -0.1036 0.5479 0.2165
0.000 0.5184 0.00805 0.00183 -0.1030 0.5389 0.2437
0.250 0.5443 0.00803 0.00185 -0.1025 0.5288 0.2662
0.500 0.5697 0.00806 0.00189 -0.1019 0.5183 0.2856
0.750 0.5945 0.00812 0.00193 -0.1012 0.5049 0.3008
1.000 0.6185 0.00822 0.00199 -0.1003 0.4869 0.3141
1.250 0.6415 0.00837 0.00207 -0.0993 0.4644 0.3270
1.500 0.6629 0.00859 0.00219 -0.0980 0.4378 0.3385
1.750 0.6843 0.00881 0.00232 -0.0967 0.4114 0.3507
2.000 0.7045 0.00906 0.00247 -0.0952 0.3853 0.3661
2.250 0.7252 0.00928 0.00263 -0.0937 0.3634 0.3822
2.500 0.7466 0.00946 0.00277 -0.0925 0.3477 0.3966
3.000 0.7904 0.00974 0.00303 -0.0901 0.3259 0.4318
3.250 0.8111 0.00989 0.00318 -0.0886 0.3158 0.4514
3.500 0.8319 0.00998 0.00330 -0.0872 0.3083 0.4742
3.750 0.8492 0.01011 0.00345 -0.0851 0.2984 0.5046
4.000 0.8681 0.01015 0.00359 -0.0833 0.2912 0.5489
4.250 0.8843 0.01017 0.00377 -0.0811 0.2844 0.6246
4.750 1.0123 0.01014 0.00448 -0.0970 0.2709 1.0000
5.000 1.0277 0.01032 0.00463 -0.0945 0.2659 1.0000
5.250 1.0451 0.01048 0.00477 -0.0924 0.2621 1.0000
5.500 1.0630 0.01065 0.00493 -0.0904 0.2575 1.0000
5.750 1.0805 0.01085 0.00511 -0.0885 0.2528 1.0000
6.000 1.0978 0.01109 0.00531 -0.0865 0.2480 1.0000
6.250 1.1174 0.01127 0.00550 -0.0850 0.2447 1.0000
6.500 1.1367 0.01149 0.00571 -0.0834 0.2406 1.0000
6.750 1.1549 0.01175 0.00594 -0.0818 0.2357 1.0000
7.000 1.1733 0.01203 0.00620 -0.0802 0.2312 1.0000
7.250 1.1928 0.01228 0.00645 -0.0788 0.2274 1.0000
7.500 1.2116 0.01257 0.00672 -0.0773 0.2222 1.0000
7.750 1.2291 0.01292 0.00705 -0.0757 0.2169 1.0000
8.000 1.2481 0.01323 0.00736 -0.0744 0.2126 1.0000
8.250 1.2666 0.01357 0.00769 -0.0730 0.2072 1.0000
8.500 1.2832 0.01401 0.00809 -0.0714 0.2012 1.0000
8.750 1.3016 0.01437 0.00846 -0.0701 0.1965 1.0000
9.000 1.3181 0.01485 0.00890 -0.0685 0.1893 1.0000
9.250 1.3345 0.01534 0.00938 -0.0670 0.1836 1.0000
9.500 1.3513 0.01583 0.00985 -0.0656 0.1774 1.0000
9.750 1.3658 0.01645 0.01043 -0.0640 0.1703 1.0000
10.000 1.3809 0.01706 0.01102 -0.0625 0.1626 1.0000
10.250 1.3952 0.01773 0.01167 -0.0609 0.1568 1.0000
10.500 1.4101 0.01838 0.01231 -0.0595 0.1504 1.0000
10.750 1.4227 0.01919 0.01308 -0.0579 0.1438 1.0000
11.000 1.4385 0.01983 0.01374 -0.0567 0.1400 1.0000
11.250 1.4520 0.02063 0.01452 -0.0553 0.1350 1.0000
11.500 1.4651 0.02146 0.01535 -0.0539 0.1303 1.0000
11.750 1.4799 0.02222 0.01613 -0.0528 0.1276 1.0000
12.000 1.4938 0.02304 0.01697 -0.0516 0.1244 1.0000
12.250 1.5042 0.02412 0.01803 -0.0502 0.1191 1.0000
12.500 1.5181 0.02499 0.01892 -0.0491 0.1167 1.0000
12.750 1.5310 0.02594 0.01989 -0.0480 0.1139 1.0000
13.000 1.5435 0.02695 0.02092 -0.0469 0.1114 1.0000
13.250 1.5536 0.02815 0.02213 -0.0457 0.1077 1.0000
13.500 1.5653 0.02927 0.02327 -0.0447 0.1055 1.0000
13.750 1.5781 0.03031 0.02435 -0.0439 0.1037 1.0000
14.000 1.5892 0.03150 0.02558 -0.0429 0.1014 1.0000
14.250 1.5989 0.03283 0.02692 -0.0420 0.0985 1.0000
14.500 1.6069 0.03433 0.02843 -0.0410 0.0953 1.0000
14.750 1.6177 0.03561 0.02975 -0.0402 0.0935 1.0000
15.000 1.6263 0.03708 0.03125 -0.0393 0.0896 1.0000
15.250 1.6322 0.03882 0.03300 -0.0384 0.0859 1.0000
15.500 1.6388 0.04053 0.03473 -0.0376 0.0813 1.0000
15.750 1.6409 0.04267 0.03686 -0.0366 0.0755 1.0000
16.000 1.6359 0.04551 0.03965 -0.0355 0.0646 1.0000
16.250 1.6078 0.05073 0.04474 -0.0339 0.0434 1.0000
16.500 1.5834 0.05586 0.04982 -0.0329 0.0289 1.0000
16.750 1.5656 0.06052 0.05449 -0.0323 0.0199 1.0000
17.000 1.5585 0.06412 0.05815 -0.0321 0.0170 1.0000
17.250 1.5560 0.06725 0.06134 -0.0320 0.0158 1.0000
17.500 1.5522 0.07060 0.06476 -0.0320 0.0148 1.0000
17.750 1.5482 0.07404 0.06827 -0.0321 0.0142 1.0000
18.000 1.5431 0.07768 0.07199 -0.0324 0.0135 1.0000
18.250 1.5376 0.08141 0.07580 -0.0328 0.0130 1.0000
18.500 1.5320 0.08521 0.07968 -0.0332 0.0128 1.0000
18.750 1.5234 0.08948 0.08404 -0.0339 0.0123 1.0000
19.000 1.5158 0.09366 0.08831 -0.0347 0.0122 1.0000
19.250 1.5045 0.09841 0.09315 -0.0356 0.0118 1.0000
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