GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il) Reynolds number: 100,000 Max Cl/Cd: 46.47 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe289-il-100000-n5.txt Download as CSV file: xf-goe289-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0645 0.09829 0.09306 -0.0947 0.9293 0.0544
-10.000 -0.0552 0.09369 0.08843 -0.0989 0.9213 0.0541
-9.750 -0.0675 0.08381 0.07851 -0.1074 0.9140 0.0516
-9.500 -0.0596 0.07910 0.07376 -0.1115 0.9050 0.0514
-9.250 -0.0517 0.07383 0.06846 -0.1167 0.8967 0.0511
-9.000 -0.0573 0.06761 0.06222 -0.1215 0.8845 0.0508
-8.750 -0.1280 0.05136 0.04580 -0.1348 0.8643 0.0496
-8.500 -0.1730 0.04361 0.03753 -0.1375 0.8474 0.0491
-8.250 -0.1833 0.03955 0.03301 -0.1369 0.8356 0.0492
-8.000 -0.1780 0.03641 0.02939 -0.1366 0.8268 0.0498
-7.750 -0.1719 0.03423 0.02682 -0.1350 0.8162 0.0505
-7.500 -0.1551 0.03193 0.02401 -0.1347 0.8091 0.0514
-7.250 -0.1406 0.03063 0.02251 -0.1332 0.7993 0.0521
-7.000 -0.1158 0.02941 0.02114 -0.1333 0.7927 0.0529
-6.750 -0.0975 0.02838 0.01995 -0.1321 0.7837 0.0535
-6.500 -0.0730 0.02726 0.01863 -0.1319 0.7767 0.0543
-6.250 -0.0516 0.02634 0.01754 -0.1310 0.7686 0.0553
-6.000 -0.0278 0.02541 0.01642 -0.1304 0.7610 0.0564
-5.750 -0.0031 0.02456 0.01536 -0.1300 0.7539 0.0577
-5.500 0.0190 0.02387 0.01455 -0.1290 0.7455 0.0590
-5.250 0.0474 0.02324 0.01383 -0.1292 0.7395 0.0613
-5.000 0.0669 0.02283 0.01336 -0.1278 0.7304 0.0640
-4.750 0.0937 0.02225 0.01264 -0.1276 0.7236 0.0673
-4.500 0.1155 0.02186 0.01223 -0.1265 0.7154 0.0707
-4.250 0.1401 0.02140 0.01165 -0.1259 0.7080 0.0757
-4.000 0.1650 0.02100 0.01122 -0.1253 0.7008 0.0832
-3.750 0.1871 0.02069 0.01089 -0.1242 0.6925 0.0945
-3.500 0.2156 0.02038 0.01050 -0.1243 0.6863 0.1124
-3.250 0.2359 0.02027 0.01038 -0.1229 0.6773 0.1274
-3.000 0.2626 0.02008 0.01007 -0.1226 0.6703 0.1421
-2.750 0.2853 0.01997 0.00991 -0.1217 0.6624 0.1567
-2.500 0.3093 0.01980 0.00973 -0.1210 0.6547 0.1732
-2.250 0.3343 0.01962 0.00953 -0.1205 0.6478 0.1920
-2.000 0.3558 0.01948 0.00945 -0.1193 0.6395 0.2102
-1.750 0.3826 0.01924 0.00922 -0.1191 0.6332 0.2305
-1.500 0.4024 0.01916 0.00922 -0.1176 0.6248 0.2513
-1.250 0.4276 0.01901 0.00909 -0.1170 0.6180 0.2815
-1.000 0.4503 0.01896 0.00910 -0.1160 0.6106 0.3177
-0.750 0.4738 0.01893 0.00908 -0.1152 0.6033 0.3549
-0.500 0.5002 0.01887 0.00896 -0.1148 0.5973 0.3895
-0.250 0.5215 0.01888 0.00902 -0.1136 0.5894 0.4184
0.000 0.5483 0.01878 0.00892 -0.1133 0.5833 0.4502
0.500 0.5942 0.01868 0.00903 -0.1114 0.5694 0.5322
0.750 0.6199 0.01848 0.00900 -0.1108 0.5639 0.6142
1.000 0.6438 0.01824 0.00924 -0.1098 0.5565 0.7560
1.500 0.7482 0.01846 0.00936 -0.1198 0.5419 1.0000
1.750 0.7691 0.01868 0.00945 -0.1186 0.5355 1.0000
2.250 0.8117 0.01916 0.00968 -0.1163 0.5233 1.0000
2.500 0.8334 0.01940 0.00981 -0.1152 0.5174 1.0000
2.750 0.8583 0.01961 0.00986 -0.1147 0.5124 1.0000
3.000 0.8750 0.01995 0.01018 -0.1128 0.5056 1.0000
3.250 0.8963 0.02020 0.01034 -0.1117 0.4997 1.0000
3.500 0.9204 0.02045 0.01046 -0.1111 0.4947 1.0000
3.750 0.9364 0.02082 0.01083 -0.1091 0.4882 1.0000
4.000 0.9573 0.02112 0.01105 -0.1079 0.4828 1.0000
4.500 0.9972 0.02180 0.01165 -0.1055 0.4726 1.0000
4.750 1.0161 0.02215 0.01196 -0.1040 0.4672 1.0000
5.000 1.0398 0.02242 0.01214 -0.1034 0.4627 1.0000
5.250 1.0554 0.02286 0.01258 -0.1015 0.4574 1.0000
5.500 1.0702 0.02327 0.01300 -0.0994 0.4519 1.0000
5.750 1.0908 0.02361 0.01328 -0.0983 0.4475 1.0000
6.000 1.1134 0.02396 0.01358 -0.0976 0.4436 1.0000
6.250 1.1237 0.02453 0.01422 -0.0949 0.4387 1.0000
6.500 1.1398 0.02500 0.01470 -0.0932 0.4342 1.0000
6.750 1.1611 0.02538 0.01503 -0.0923 0.4303 1.0000
7.000 1.1818 0.02580 0.01543 -0.0914 0.4266 1.0000
7.250 1.1898 0.02651 0.01622 -0.0886 0.4218 1.0000
7.500 1.2047 0.02706 0.01680 -0.0869 0.4175 1.0000
7.750 1.2255 0.02749 0.01722 -0.0861 0.4140 1.0000
8.000 1.2503 0.02787 0.01755 -0.0859 0.4111 1.0000
8.250 1.2548 0.02882 0.01864 -0.0829 0.4071 1.0000
8.500 1.2653 0.02964 0.01953 -0.0808 0.4032 1.0000
8.750 1.2816 0.03028 0.02022 -0.0795 0.4000 1.0000
9.000 1.3035 0.03073 0.02066 -0.0790 0.3970 1.0000
9.250 1.3247 0.03126 0.02120 -0.0784 0.3942 1.0000
9.500 1.3212 0.03266 0.02277 -0.0749 0.3901 1.0000
9.750 1.3272 0.03379 0.02401 -0.0727 0.3865 1.0000
10.000 1.3411 0.03463 0.02490 -0.0714 0.3835 1.0000
10.250 1.3620 0.03520 0.02550 -0.0709 0.3810 1.0000
10.500 1.3888 0.03556 0.02587 -0.0710 0.3790 1.0000
10.750 1.3776 0.03765 0.02816 -0.0674 0.3755 1.0000
11.000 1.3648 0.04003 0.03072 -0.0641 0.3716 1.0000
11.250 1.3666 0.04172 0.03251 -0.0622 0.3683 1.0000
11.500 1.3821 0.04260 0.03345 -0.0613 0.3657 1.0000
11.750 1.4072 0.04294 0.03383 -0.0612 0.3637 1.0000
12.000 1.4261 0.04374 0.03469 -0.0607 0.3617 1.0000
12.250 1.2945 0.05640 0.04775 -0.0532 0.3522 1.0000
12.500 1.3009 0.05830 0.04973 -0.0525 0.3494 1.0000
12.750 1.3271 0.05825 0.04975 -0.0522 0.3479 1.0000
13.000 1.3591 0.05772 0.04926 -0.0521 0.3467 1.0000
13.500 1.0156 0.10982 0.10171 -0.0562 0.3024 1.0000
13.750 1.0316 0.11082 0.10278 -0.0559 0.3006 1.0000
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Polar data table (+)
Polar graphs
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