GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il) Reynolds number: 100,000 Max Cl/Cd: 38.61 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe289-il-100000.txt Download as CSV file: xf-goe289-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1607 0.12784 0.12329 -0.0589 0.9737 0.1153
-10.250 -0.1585 0.12536 0.12081 -0.0661 0.9674 0.1201
-10.000 -0.1680 0.12264 0.11813 -0.0744 0.9590 0.1215
-9.750 -0.1186 0.11582 0.11123 -0.0747 0.9572 0.1235
-9.500 -0.0951 0.11218 0.10757 -0.0766 0.9496 0.1262
-9.250 -0.0734 0.10839 0.10375 -0.0811 0.9445 0.1304
-9.000 -0.0916 0.10698 0.10238 -0.0890 0.9329 0.1358
-8.750 -0.0637 0.10115 0.09653 -0.0923 0.9292 0.1380
-8.500 -0.0203 0.09671 0.09203 -0.0946 0.9271 0.1422
-8.250 -0.0080 0.09386 0.08918 -0.0969 0.9176 0.1467
-8.000 -0.0540 0.09313 0.08853 -0.1060 0.9009 0.1525
-7.750 0.0024 0.08644 0.08177 -0.1074 0.9013 0.1548
-7.500 0.0419 0.08246 0.07774 -0.1102 0.8977 0.1585
-7.250 0.0648 0.07861 0.07384 -0.1161 0.8929 0.1652
-7.000 -0.0164 0.07824 0.07354 -0.1189 0.8661 0.1700
-6.750 0.0325 0.07380 0.06909 -0.1177 0.8641 0.1719
-6.500 -0.0573 0.05657 0.05131 -0.1277 0.8442 0.1064
-6.250 -0.0885 0.04879 0.04292 -0.1262 0.8315 0.0959
-6.000 -0.0723 0.04437 0.03794 -0.1273 0.8253 0.0942
-5.750 -0.0657 0.04201 0.03525 -0.1253 0.8155 0.0942
-5.500 -0.0440 0.03902 0.03172 -0.1254 0.8090 0.0947
-5.250 -0.0089 0.03576 0.02799 -0.1273 0.8057 0.0954
-5.000 -0.0035 0.03478 0.02688 -0.1239 0.7939 0.0962
-4.750 0.0354 0.03273 0.02461 -0.1258 0.7900 0.0985
-4.500 0.0502 0.03198 0.02371 -0.1236 0.7801 0.1005
-4.250 0.0842 0.03046 0.02184 -0.1243 0.7746 0.1053
-4.000 0.1272 0.02885 0.02011 -0.1266 0.7712 0.1126
-3.750 0.1367 0.02867 0.01982 -0.1233 0.7597 0.1180
-3.500 0.1769 0.02718 0.01825 -0.1249 0.7553 0.1314
-3.250 0.1931 0.02673 0.01778 -0.1228 0.7461 0.1492
-3.000 0.2237 0.02577 0.01688 -0.1229 0.7397 0.1818
-2.750 0.2659 0.02477 0.01585 -0.1250 0.7358 0.2109
-2.500 0.2732 0.02508 0.01618 -0.1215 0.7243 0.2257
-2.250 0.3125 0.02455 0.01561 -0.1231 0.7194 0.2565
-2.000 0.3244 0.02486 0.01597 -0.1204 0.7094 0.2753
-1.750 0.3581 0.02438 0.01557 -0.1210 0.7034 0.2996
-1.500 0.3835 0.02424 0.01544 -0.1203 0.6962 0.3239
-1.250 0.4043 0.02415 0.01543 -0.1188 0.6878 0.3540
-1.000 0.4426 0.02337 0.01473 -0.1201 0.6831 0.4132
-0.750 0.4494 0.02360 0.01518 -0.1165 0.6730 0.4583
-0.500 0.4825 0.02294 0.01473 -0.1168 0.6674 0.5257
-0.250 0.5023 0.02293 0.01492 -0.1151 0.6597 0.5863
0.000 0.5259 0.02262 0.01493 -0.1139 0.6522 0.6746
0.250 0.6593 0.02141 0.01396 -0.1333 0.6462 1.0000
0.500 0.6653 0.02203 0.01447 -0.1297 0.6367 1.0000
0.750 0.7001 0.02192 0.01407 -0.1307 0.6313 1.0000
1.000 0.7093 0.02251 0.01459 -0.1276 0.6225 1.0000
1.250 0.7378 0.02255 0.01443 -0.1275 0.6161 1.0000
1.500 0.7626 0.02277 0.01449 -0.1269 0.6096 1.0000
1.750 0.7767 0.02326 0.01490 -0.1246 0.6016 1.0000
2.000 0.8130 0.02315 0.01458 -0.1258 0.5966 1.0000
2.250 0.8202 0.02389 0.01532 -0.1224 0.5882 1.0000
2.500 0.8490 0.02397 0.01525 -0.1224 0.5820 1.0000
2.750 0.8772 0.02416 0.01529 -0.1224 0.5762 1.0000
3.000 0.8868 0.02483 0.01597 -0.1194 0.5681 1.0000
3.250 0.9219 0.02481 0.01578 -0.1205 0.5631 1.0000
3.500 0.9327 0.02559 0.01658 -0.1178 0.5562 1.0000
3.750 0.9522 0.02604 0.01698 -0.1165 0.5496 1.0000
4.000 0.9911 0.02597 0.01673 -0.1182 0.5451 1.0000
4.250 0.9914 0.02706 0.01791 -0.1139 0.5375 1.0000
4.500 1.0156 0.02740 0.01818 -0.1133 0.5317 1.0000
4.750 1.0563 0.02736 0.01796 -0.1154 0.5276 1.0000
5.000 1.0479 0.02881 0.01958 -0.1099 0.5204 1.0000
5.250 1.0678 0.02938 0.02012 -0.1088 0.5151 1.0000
5.500 1.1072 0.02940 0.02001 -0.1106 0.5113 1.0000
5.750 1.1010 0.03091 0.02165 -0.1057 0.5051 1.0000
6.000 1.1081 0.03190 0.02268 -0.1028 0.4993 1.0000
6.250 1.1451 0.03194 0.02264 -0.1042 0.4954 1.0000
6.500 1.1728 0.03248 0.02314 -0.1044 0.4917 1.0000
6.750 1.1177 0.03573 0.02664 -0.0930 0.4845 1.0000
7.000 1.1379 0.03641 0.02733 -0.0921 0.4805 1.0000
7.250 1.1847 0.03629 0.02714 -0.0950 0.4777 1.0000
7.500 0.9239 0.05571 0.04700 -0.0702 0.4575 1.0000
7.750 0.9822 0.05265 0.04388 -0.0709 0.4578 1.0000
8.000 1.0478 0.04948 0.04067 -0.0727 0.4581 1.0000
8.250 1.1307 0.04584 0.03697 -0.0767 0.4585 1.0000
9.500 0.6109 0.12096 0.11287 -0.0720 0.4686 1.0000
9.750 0.6254 0.12296 0.11488 -0.0720 0.4642 1.0000
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Polar data table (+)
Polar graphs
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