GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il) Reynolds number: 200,000 Max Cl/Cd: 65.9 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe289-il-200000.txt Download as CSV file: xf-goe289-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1161 0.12218 0.11868 -0.0720 0.9758 0.0694
-11.250 -0.1051 0.11804 0.11452 -0.0781 0.9719 0.0728
-11.000 -0.1124 0.11277 0.10928 -0.0863 0.9652 0.0743
-10.750 -0.0806 0.10910 0.10559 -0.0869 0.9614 0.0752
-10.500 -0.0540 0.10555 0.10201 -0.0898 0.9583 0.0766
-10.250 -0.0343 0.10210 0.09855 -0.0932 0.9532 0.0788
-10.000 -0.0502 0.09664 0.09310 -0.1068 0.9445 0.0837
-9.750 -0.0188 0.09198 0.08842 -0.1077 0.9424 0.0847
-9.500 0.0111 0.08913 0.08554 -0.1090 0.9360 0.0860
-9.250 0.0387 0.08569 0.08208 -0.1131 0.9305 0.0879
-9.000 0.0642 0.08141 0.07774 -0.1202 0.9259 0.0915
-8.750 0.0537 0.07386 0.07018 -0.1338 0.9112 0.0957
-8.500 -0.0638 0.04689 0.04279 -0.1526 0.8812 0.0658
-8.250 -0.0297 0.04647 0.04240 -0.1534 0.8743 0.0667
-8.000 -0.1326 0.03237 0.02678 -0.1491 0.8522 0.0579
-7.750 -0.1217 0.03006 0.02410 -0.1477 0.8427 0.0579
-7.500 -0.1079 0.02819 0.02197 -0.1462 0.8335 0.0582
-7.250 -0.0900 0.02641 0.01989 -0.1452 0.8251 0.0584
-7.000 -0.0724 0.02491 0.01812 -0.1438 0.8163 0.0585
-6.750 -0.0507 0.02358 0.01656 -0.1430 0.8081 0.0589
-6.500 -0.0290 0.02251 0.01530 -0.1420 0.7998 0.0594
-6.250 -0.0057 0.02155 0.01417 -0.1412 0.7914 0.0600
-6.000 0.0182 0.02071 0.01318 -0.1405 0.7834 0.0610
-5.750 0.0419 0.01994 0.01225 -0.1396 0.7748 0.0620
-5.500 0.0673 0.01929 0.01144 -0.1391 0.7671 0.0636
-5.250 0.0910 0.01878 0.01076 -0.1381 0.7581 0.0651
-5.000 0.1161 0.01805 0.01002 -0.1377 0.7506 0.0673
-4.750 0.1387 0.01762 0.00957 -0.1366 0.7414 0.0695
-4.500 0.1655 0.01718 0.00900 -0.1362 0.7341 0.0724
-4.250 0.1865 0.01674 0.00855 -0.1348 0.7247 0.0760
-4.000 0.2143 0.01641 0.00812 -0.1347 0.7177 0.0820
-3.750 0.2344 0.01609 0.00787 -0.1331 0.7082 0.0914
-3.500 0.2611 0.01579 0.00758 -0.1327 0.7009 0.1182
-3.250 0.2829 0.01567 0.00750 -0.1315 0.6919 0.1420
-3.000 0.3093 0.01555 0.00729 -0.1312 0.6844 0.1578
-2.750 0.3331 0.01552 0.00718 -0.1303 0.6762 0.1700
-2.500 0.3577 0.01533 0.00700 -0.1296 0.6684 0.1833
-2.250 0.3823 0.01521 0.00687 -0.1290 0.6612 0.1983
-2.000 0.4054 0.01505 0.00675 -0.1280 0.6531 0.2135
-1.750 0.4326 0.01490 0.00657 -0.1279 0.6469 0.2342
-1.500 0.4529 0.01474 0.00656 -0.1264 0.6385 0.2618
-1.250 0.4778 0.01457 0.00651 -0.1258 0.6318 0.3127
-1.000 0.5002 0.01453 0.00660 -0.1247 0.6245 0.3693
-0.750 0.5234 0.01446 0.00657 -0.1237 0.6173 0.4109
-0.500 0.5492 0.01439 0.00649 -0.1232 0.6113 0.4447
-0.250 0.5700 0.01431 0.00652 -0.1218 0.6035 0.4752
0.000 0.5945 0.01418 0.00645 -0.1210 0.5971 0.5125
0.250 0.6149 0.01406 0.00652 -0.1195 0.5900 0.5623
0.500 0.6347 0.01383 0.00657 -0.1177 0.5832 0.6509
0.750 0.7552 0.01346 0.00671 -0.1366 0.5736 0.9972
1.000 0.7792 0.01361 0.00673 -0.1359 0.5665 1.0000
1.250 0.8041 0.01379 0.00672 -0.1354 0.5604 1.0000
1.500 0.8224 0.01395 0.00685 -0.1335 0.5530 1.0000
1.750 0.8457 0.01412 0.00687 -0.1327 0.5467 1.0000
2.000 0.8677 0.01434 0.00700 -0.1315 0.5403 1.0000
2.250 0.8882 0.01453 0.00712 -0.1302 0.5336 1.0000
2.500 0.9138 0.01475 0.00718 -0.1298 0.5280 1.0000
2.750 0.9327 0.01497 0.00740 -0.1281 0.5213 1.0000
3.000 0.9543 0.01517 0.00753 -0.1269 0.5149 1.0000
3.250 0.9804 0.01544 0.00764 -0.1266 0.5093 1.0000
3.500 0.9972 0.01565 0.00788 -0.1246 0.5024 1.0000
3.750 1.0198 0.01587 0.00803 -0.1236 0.4966 1.0000
4.000 1.0444 0.01617 0.00822 -0.1231 0.4912 1.0000
4.250 1.0622 0.01642 0.00850 -0.1213 0.4850 1.0000
4.500 1.0850 0.01667 0.00868 -0.1204 0.4796 1.0000
4.750 1.1106 0.01699 0.00891 -0.1202 0.4746 1.0000
5.000 1.1269 0.01726 0.00923 -0.1181 0.4687 1.0000
5.250 1.1487 0.01752 0.00945 -0.1171 0.4635 1.0000
5.500 1.1770 0.01786 0.00965 -0.1174 0.4588 1.0000
5.750 1.1909 0.01816 0.01005 -0.1149 0.4535 1.0000
6.000 1.2111 0.01846 0.01035 -0.1137 0.4486 1.0000
6.250 1.2360 0.01877 0.01059 -0.1133 0.4444 1.0000
6.500 1.2590 0.01917 0.01098 -0.1127 0.4403 1.0000
6.750 1.2746 0.01954 0.01142 -0.1107 0.4357 1.0000
7.000 1.2953 0.01987 0.01176 -0.1096 0.4314 1.0000
7.250 1.3208 0.02021 0.01204 -0.1094 0.4278 1.0000
7.500 1.3435 0.02065 0.01248 -0.1088 0.4239 1.0000
7.750 1.3563 0.02106 0.01300 -0.1064 0.4198 1.0000
8.000 1.3751 0.02145 0.01342 -0.1050 0.4159 1.0000
8.250 1.3990 0.02182 0.01378 -0.1046 0.4126 1.0000
8.500 1.4308 0.02229 0.01417 -0.1058 0.4095 1.0000
8.750 1.4423 0.02282 0.01484 -0.1032 0.4064 1.0000
9.000 1.4533 0.02333 0.01545 -0.1006 0.4032 1.0000
9.250 1.4696 0.02379 0.01597 -0.0989 0.3999 1.0000
9.500 1.4919 0.02420 0.01641 -0.0983 0.3969 1.0000
9.750 1.5248 0.02462 0.01676 -0.0997 0.3937 1.0000
10.000 1.5309 0.02520 0.01746 -0.0963 0.3902 1.0000
10.250 1.5328 0.02573 0.01812 -0.0922 0.3862 1.0000
10.500 1.5460 0.02607 0.01849 -0.0901 0.3819 1.0000
10.750 1.5802 0.02617 0.01843 -0.0915 0.3764 1.0000
11.000 1.5722 0.02692 0.01939 -0.0862 0.3730 1.0000
11.250 1.5763 0.02759 0.02018 -0.0830 0.3691 1.0000
11.500 1.5901 0.02797 0.02059 -0.0813 0.3647 1.0000
11.750 1.6171 0.02818 0.02070 -0.0815 0.3599 1.0000
12.000 1.6071 0.02925 0.02198 -0.0767 0.3560 1.0000
12.250 1.6092 0.03005 0.02288 -0.0738 0.3514 1.0000
12.500 1.6249 0.03041 0.02323 -0.0725 0.3467 1.0000
12.750 1.6332 0.03121 0.02408 -0.0705 0.3423 1.0000
13.000 1.6267 0.03258 0.02564 -0.0671 0.3379 1.0000
13.250 1.6313 0.03347 0.02658 -0.0650 0.3330 1.0000
13.500 1.6502 0.03384 0.02689 -0.0643 0.3279 1.0000
13.750 1.6372 0.03586 0.02914 -0.0609 0.3237 1.0000
14.000 1.6341 0.03743 0.03083 -0.0586 0.3184 1.0000
14.250 1.6417 0.03832 0.03168 -0.0572 0.3117 1.0000
14.500 1.6284 0.04092 0.03450 -0.0548 0.3068 1.0000
14.750 1.6249 0.04286 0.03651 -0.0531 0.3000 1.0000
15.000 1.6188 0.04527 0.03902 -0.0516 0.2935 1.0000
15.250 1.6063 0.04837 0.04222 -0.0501 0.2848 1.0000
15.500 1.5955 0.05164 0.04561 -0.0490 0.2769 1.0000
15.750 1.5829 0.05521 0.04922 -0.0481 0.2661 1.0000
16.000 1.5638 0.05985 0.05400 -0.0476 0.2548 1.0000
16.250 1.5456 0.06462 0.05888 -0.0472 0.2427 1.0000
16.500 1.5228 0.07009 0.06440 -0.0471 0.2266 1.0000
16.750 1.4966 0.07615 0.07045 -0.0472 0.2065 1.0000
17.000 1.4681 0.08263 0.07687 -0.0476 0.1852 1.0000
17.250 1.4372 0.08961 0.08378 -0.0482 0.1641 1.0000
17.500 1.4029 0.09723 0.09132 -0.0492 0.1435 1.0000
17.750 1.3694 0.10499 0.09902 -0.0505 0.1232 1.0000
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