GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il) Reynolds number: 500,000 Max Cl/Cd: 92.08 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe289-il-500000.txt Download as CSV file: xf-goe289-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 289 (MVA 289) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0538 0.09399 0.09154 -0.1030 0.9439 0.0450
-10.750 -0.1694 0.05665 0.05406 -0.1322 0.9350 0.0394
-10.500 -0.2661 0.03234 0.02872 -0.1629 0.8957 0.0359
-10.250 -0.2847 0.02903 0.02493 -0.1601 0.8769 0.0355
-10.000 -0.2839 0.02716 0.02278 -0.1576 0.8621 0.0355
-9.750 -0.2753 0.02577 0.02116 -0.1557 0.8489 0.0357
-9.500 -0.2642 0.02443 0.01959 -0.1539 0.8365 0.0359
-9.250 -0.2529 0.02301 0.01790 -0.1520 0.8241 0.0358
-9.000 -0.2385 0.02184 0.01651 -0.1503 0.8123 0.0359
-8.750 -0.2212 0.02084 0.01530 -0.1489 0.8018 0.0360
-8.500 -0.2032 0.01992 0.01420 -0.1475 0.7909 0.0362
-8.250 -0.1837 0.01909 0.01320 -0.1463 0.7812 0.0364
-8.000 -0.1631 0.01836 0.01230 -0.1452 0.7720 0.0366
-7.750 -0.1422 0.01766 0.01146 -0.1441 0.7630 0.0368
-7.500 -0.1204 0.01704 0.01070 -0.1431 0.7545 0.0372
-7.250 -0.0984 0.01647 0.01001 -0.1421 0.7463 0.0375
-7.000 -0.0755 0.01602 0.00944 -0.1412 0.7384 0.0379
-6.750 -0.0522 0.01564 0.00895 -0.1403 0.7309 0.0384
-6.500 -0.0289 0.01525 0.00845 -0.1394 0.7230 0.0386
-6.250 -0.0066 0.01463 0.00775 -0.1385 0.7160 0.0390
-6.000 0.0149 0.01402 0.00712 -0.1374 0.7083 0.0396
-5.750 0.0378 0.01362 0.00664 -0.1364 0.7010 0.0401
-5.500 0.0608 0.01326 0.00626 -0.1355 0.6935 0.0407
-5.250 0.0841 0.01296 0.00591 -0.1346 0.6858 0.0414
-5.000 0.1077 0.01269 0.00558 -0.1337 0.6784 0.0421
-4.750 0.1313 0.01243 0.00527 -0.1328 0.6703 0.0430
-4.500 0.1554 0.01224 0.00498 -0.1320 0.6630 0.0438
-4.250 0.1787 0.01195 0.00467 -0.1310 0.6547 0.0450
-3.750 0.2267 0.01153 0.00417 -0.1293 0.6393 0.0489
-3.500 0.2506 0.01136 0.00394 -0.1284 0.6316 0.0520
-3.250 0.2747 0.01116 0.00375 -0.1276 0.6238 0.0584
-3.000 0.2976 0.01089 0.00361 -0.1266 0.6158 0.0887
-2.750 0.3221 0.01079 0.00356 -0.1259 0.6082 0.1134
-2.500 0.3468 0.01075 0.00351 -0.1252 0.6004 0.1257
-2.250 0.3717 0.01075 0.00346 -0.1246 0.5932 0.1357
-2.000 0.3961 0.01068 0.00341 -0.1238 0.5856 0.1464
-1.500 0.4447 0.01061 0.00330 -0.1223 0.5711 0.1662
-1.250 0.4684 0.01057 0.00325 -0.1215 0.5640 0.1796
-1.000 0.4923 0.01050 0.00322 -0.1207 0.5577 0.1998
-0.750 0.5154 0.01036 0.00321 -0.1198 0.5511 0.2422
-0.500 0.5376 0.01028 0.00327 -0.1187 0.5448 0.3094
-0.250 0.5618 0.01025 0.00332 -0.1180 0.5384 0.3485
0.000 0.5853 0.01027 0.00337 -0.1171 0.5319 0.3761
0.250 0.6087 0.01033 0.00341 -0.1162 0.5259 0.3992
0.500 0.6325 0.01032 0.00345 -0.1153 0.5199 0.4205
0.750 0.6554 0.01035 0.00348 -0.1144 0.5140 0.4389
1.000 0.6781 0.01038 0.00354 -0.1133 0.5085 0.4600
1.250 0.7003 0.01031 0.00360 -0.1122 0.5028 0.4947
1.500 0.7195 0.01020 0.00369 -0.1105 0.4972 0.5716
1.750 0.7341 0.00997 0.00382 -0.1078 0.4919 0.7078
2.000 0.8621 0.00990 0.00425 -0.1295 0.4815 1.0000
2.250 0.8816 0.01009 0.00433 -0.1279 0.4759 1.0000
2.500 0.9031 0.01018 0.00441 -0.1266 0.4705 1.0000
2.750 0.9233 0.01031 0.00450 -0.1251 0.4648 1.0000
3.000 0.9425 0.01052 0.00461 -0.1234 0.4594 1.0000
3.250 0.9634 0.01063 0.00471 -0.1220 0.4541 1.0000
3.500 0.9829 0.01078 0.00483 -0.1204 0.4485 1.0000
3.750 0.9995 0.01099 0.00496 -0.1182 0.4430 1.0000
4.000 1.0181 0.01111 0.00508 -0.1164 0.4378 1.0000
4.250 1.0358 0.01127 0.00521 -0.1144 0.4320 1.0000
4.500 1.0526 0.01150 0.00536 -0.1124 0.4268 1.0000
4.750 1.0720 0.01167 0.00553 -0.1108 0.4219 1.0000
5.000 1.0912 0.01185 0.00570 -0.1092 0.4167 1.0000
5.250 1.1092 0.01209 0.00589 -0.1075 0.4119 1.0000
5.500 1.1282 0.01234 0.00612 -0.1060 0.4072 1.0000
5.750 1.1484 0.01253 0.00632 -0.1047 0.4027 1.0000
6.000 1.1673 0.01278 0.00655 -0.1032 0.3980 1.0000
6.250 1.1852 0.01311 0.00682 -0.1016 0.3935 1.0000
6.500 1.2055 0.01334 0.00707 -0.1004 0.3896 1.0000
6.750 1.2252 0.01359 0.00734 -0.0992 0.3854 1.0000
7.000 1.2437 0.01390 0.00762 -0.0978 0.3812 1.0000
7.250 1.2621 0.01428 0.00796 -0.0964 0.3772 1.0000
7.500 1.2821 0.01457 0.00827 -0.0953 0.3739 1.0000
7.750 1.3019 0.01485 0.00860 -0.0943 0.3707 1.0000
8.000 1.3211 0.01519 0.00894 -0.0931 0.3673 1.0000
8.250 1.3396 0.01557 0.00931 -0.0919 0.3641 1.0000
8.500 1.3588 0.01602 0.00971 -0.0908 0.3603 1.0000
8.750 1.3779 0.01635 0.01011 -0.0897 0.3578 1.0000
9.000 1.3951 0.01672 0.01054 -0.0884 0.3537 1.0000
9.250 1.4116 0.01717 0.01098 -0.0871 0.3493 1.0000
9.500 1.4277 0.01772 0.01148 -0.0857 0.3448 1.0000
9.750 1.4444 0.01816 0.01200 -0.0844 0.3410 1.0000
10.000 1.4609 0.01864 0.01254 -0.0832 0.3370 1.0000
10.250 1.4751 0.01924 0.01313 -0.0818 0.3322 1.0000
10.500 1.4900 0.01989 0.01376 -0.0804 0.3281 1.0000
10.750 1.5062 0.02043 0.01439 -0.0793 0.3246 1.0000
11.000 1.5217 0.02103 0.01505 -0.0782 0.3208 1.0000
11.250 1.5346 0.02179 0.01581 -0.0768 0.3163 1.0000
11.500 1.5469 0.02262 0.01664 -0.0754 0.3119 1.0000
11.750 1.5622 0.02329 0.01742 -0.0744 0.3081 1.0000
12.000 1.5752 0.02412 0.01830 -0.0733 0.3037 1.0000
12.250 1.5859 0.02511 0.01929 -0.0719 0.2994 1.0000
12.500 1.5977 0.02607 0.02032 -0.0707 0.2948 1.0000
12.750 1.6088 0.02712 0.02144 -0.0697 0.2886 1.0000
13.000 1.6140 0.02860 0.02290 -0.0681 0.2823 1.0000
13.250 1.6251 0.02975 0.02415 -0.0672 0.2749 1.0000
13.500 1.6275 0.03159 0.02598 -0.0657 0.2655 1.0000
13.750 1.6264 0.03380 0.02818 -0.0642 0.2518 1.0000
14.000 1.6210 0.03646 0.03082 -0.0626 0.2323 1.0000
14.250 1.6023 0.04042 0.03466 -0.0605 0.2065 1.0000
14.500 1.5776 0.04510 0.03921 -0.0585 0.1801 1.0000
14.750 1.5424 0.05109 0.04507 -0.0566 0.1504 1.0000
15.000 1.5109 0.05700 0.05091 -0.0552 0.1257 1.0000
15.250 1.4753 0.06370 0.05754 -0.0542 0.1009 1.0000
15.500 1.4501 0.06945 0.06327 -0.0537 0.0868 1.0000
15.750 1.4229 0.07568 0.06950 -0.0535 0.0723 1.0000
16.000 1.3961 0.08202 0.07583 -0.0535 0.0558 1.0000
16.250 1.3741 0.08791 0.08171 -0.0538 0.0439 1.0000
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Polar data table (+)
Polar graphs
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