GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il) Reynolds number: 500,000 Max Cl/Cd: 87.42 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe289-il-500000-n5.txt Download as CSV file: xf-goe289-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4331 0.05213 0.04878 -0.1259 0.9393 0.0248
-12.750 -0.4353 0.04043 0.03668 -0.1458 0.9285 0.0249
-12.500 -0.4196 0.03312 0.02897 -0.1614 0.9127 0.0250
-12.000 -0.4122 0.02829 0.02362 -0.1658 0.8774 0.0251
-11.750 -0.4157 0.02707 0.02222 -0.1629 0.8615 0.0252
-11.500 -0.4127 0.02606 0.02103 -0.1604 0.8466 0.0253
-11.250 -0.4055 0.02508 0.01988 -0.1583 0.8328 0.0253
-11.000 -0.3955 0.02422 0.01883 -0.1564 0.8186 0.0254
-10.750 -0.3841 0.02335 0.01778 -0.1545 0.8040 0.0255
-10.500 -0.3724 0.02232 0.01659 -0.1527 0.7901 0.0257
-10.250 -0.3585 0.02144 0.01558 -0.1510 0.7770 0.0258
-10.000 -0.3428 0.02069 0.01472 -0.1495 0.7656 0.0261
-9.750 -0.3257 0.02004 0.01395 -0.1481 0.7551 0.0262
-9.500 -0.3070 0.01951 0.01332 -0.1468 0.7452 0.0265
-9.250 -0.2881 0.01894 0.01265 -0.1456 0.7370 0.0267
-9.000 -0.2680 0.01844 0.01206 -0.1445 0.7289 0.0270
-8.750 -0.2478 0.01794 0.01145 -0.1434 0.7214 0.0272
-8.500 -0.2269 0.01743 0.01086 -0.1424 0.7140 0.0274
-8.250 -0.2058 0.01697 0.01029 -0.1414 0.7069 0.0276
-8.000 -0.1839 0.01653 0.00977 -0.1404 0.7007 0.0279
-7.750 -0.1617 0.01610 0.00926 -0.1395 0.6937 0.0281
-7.500 -0.1397 0.01572 0.00878 -0.1386 0.6869 0.0283
-7.250 -0.1167 0.01533 0.00833 -0.1377 0.6807 0.0286
-7.000 -0.0939 0.01498 0.00790 -0.1369 0.6739 0.0288
-6.750 -0.0709 0.01467 0.00750 -0.1360 0.6673 0.0290
-6.500 -0.0474 0.01434 0.00712 -0.1352 0.6604 0.0293
-6.250 -0.0240 0.01406 0.00676 -0.1344 0.6532 0.0295
-6.000 -0.0002 0.01380 0.00644 -0.1336 0.6465 0.0297
-5.750 0.0225 0.01344 0.00603 -0.1327 0.6386 0.0301
-5.500 0.0453 0.01314 0.00567 -0.1317 0.6311 0.0305
-5.250 0.0691 0.01287 0.00536 -0.1309 0.6231 0.0310
-5.000 0.0925 0.01267 0.00509 -0.1300 0.6150 0.0315
-4.750 0.1168 0.01248 0.00485 -0.1293 0.6061 0.0322
-4.500 0.1403 0.01233 0.00463 -0.1284 0.5972 0.0328
-4.250 0.1647 0.01218 0.00442 -0.1277 0.5881 0.0334
-4.000 0.1884 0.01207 0.00423 -0.1268 0.5797 0.0339
-3.750 0.2130 0.01195 0.00405 -0.1261 0.5717 0.0345
-3.500 0.2365 0.01183 0.00386 -0.1252 0.5644 0.0354
-3.250 0.2613 0.01170 0.00370 -0.1245 0.5572 0.0366
-3.000 0.2852 0.01162 0.00357 -0.1237 0.5496 0.0379
-2.750 0.3096 0.01154 0.00344 -0.1230 0.5427 0.0401
-2.500 0.3337 0.01142 0.00332 -0.1222 0.5361 0.0449
-2.250 0.3561 0.01122 0.00321 -0.1212 0.5301 0.0746
-2.000 0.3807 0.01112 0.00317 -0.1205 0.5242 0.0955
-1.750 0.4047 0.01108 0.00315 -0.1197 0.5175 0.1084
-1.500 0.4285 0.01107 0.00313 -0.1189 0.5117 0.1174
-1.250 0.4534 0.01106 0.00310 -0.1183 0.5058 0.1257
-1.000 0.4773 0.01105 0.00309 -0.1175 0.5001 0.1347
-0.750 0.5010 0.01107 0.00308 -0.1166 0.4951 0.1431
-0.500 0.5255 0.01103 0.00307 -0.1159 0.4898 0.1545
-0.250 0.5489 0.01102 0.00308 -0.1150 0.4840 0.1685
0.000 0.5710 0.01101 0.00309 -0.1139 0.4785 0.1890
0.250 0.5943 0.01091 0.00312 -0.1131 0.4732 0.2292
0.500 0.6164 0.01084 0.00318 -0.1120 0.4676 0.2815
0.750 0.6376 0.01085 0.00327 -0.1107 0.4624 0.3250
1.000 0.6604 0.01086 0.00333 -0.1097 0.4577 0.3508
1.250 0.6823 0.01090 0.00338 -0.1085 0.4525 0.3681
1.500 0.7028 0.01096 0.00344 -0.1070 0.4472 0.3837
1.750 0.7239 0.01102 0.00351 -0.1057 0.4421 0.3973
2.000 0.7457 0.01107 0.00358 -0.1045 0.4368 0.4103
2.250 0.7656 0.01117 0.00367 -0.1030 0.4308 0.4250
2.500 0.7856 0.01123 0.00379 -0.1015 0.4259 0.4495
2.750 0.8059 0.01122 0.00392 -0.1001 0.4209 0.4960
3.000 0.8221 0.01111 0.00411 -0.0979 0.4158 0.6091
3.250 0.8308 0.01084 0.00433 -0.0940 0.4115 0.7817
3.750 0.9697 0.01120 0.00490 -0.1125 0.3978 1.0000
4.000 0.9882 0.01140 0.00505 -0.1107 0.3932 1.0000
4.250 1.0084 0.01156 0.00520 -0.1093 0.3885 1.0000
4.500 1.0272 0.01177 0.00537 -0.1077 0.3834 1.0000
4.750 1.0449 0.01202 0.00557 -0.1060 0.3787 1.0000
5.000 1.0658 0.01221 0.00575 -0.1048 0.3749 1.0000
5.250 1.0858 0.01242 0.00595 -0.1035 0.3707 1.0000
5.500 1.1050 0.01267 0.00618 -0.1021 0.3666 1.0000
5.750 1.1230 0.01297 0.00644 -0.1005 0.3628 1.0000
6.000 1.1435 0.01320 0.00668 -0.0994 0.3595 1.0000
6.250 1.1639 0.01345 0.00693 -0.0983 0.3561 1.0000
6.500 1.1833 0.01374 0.00722 -0.0970 0.3526 1.0000
6.750 1.2016 0.01407 0.00753 -0.0956 0.3491 1.0000
7.000 1.2194 0.01444 0.00788 -0.0942 0.3458 1.0000
7.250 1.2399 0.01472 0.00819 -0.0933 0.3428 1.0000
7.500 1.2596 0.01504 0.00853 -0.0922 0.3396 1.0000
7.750 1.2784 0.01541 0.00890 -0.0910 0.3366 1.0000
8.000 1.2964 0.01581 0.00931 -0.0898 0.3337 1.0000
8.250 1.3137 0.01626 0.00976 -0.0885 0.3311 1.0000
8.500 1.3321 0.01668 0.01020 -0.0874 0.3288 1.0000
8.750 1.3518 0.01705 0.01061 -0.0865 0.3266 1.0000
9.000 1.3699 0.01750 0.01108 -0.0855 0.3228 1.0000
9.250 1.3864 0.01802 0.01162 -0.0843 0.3189 1.0000
9.500 1.4007 0.01867 0.01226 -0.0828 0.3148 1.0000
9.750 1.4179 0.01920 0.01282 -0.0818 0.3099 1.0000
10.000 1.4341 0.01980 0.01344 -0.0806 0.3052 1.0000
10.250 1.4467 0.02059 0.01422 -0.0792 0.2998 1.0000
10.500 1.4617 0.02128 0.01494 -0.0780 0.2960 1.0000
10.750 1.4782 0.02190 0.01562 -0.0771 0.2919 1.0000
11.000 1.4913 0.02274 0.01648 -0.0758 0.2868 1.0000
11.250 1.5018 0.02375 0.01748 -0.0744 0.2822 1.0000
11.500 1.5174 0.02448 0.01828 -0.0735 0.2774 1.0000
11.750 1.5299 0.02544 0.01926 -0.0724 0.2724 1.0000
12.000 1.5381 0.02670 0.02053 -0.0710 0.2670 1.0000
12.250 1.5509 0.02769 0.02158 -0.0700 0.2604 1.0000
12.500 1.5566 0.02922 0.02310 -0.0686 0.2528 1.0000
12.750 1.5647 0.03062 0.02453 -0.0674 0.2434 1.0000
13.000 1.5660 0.03261 0.02649 -0.0659 0.2308 1.0000
13.250 1.5644 0.03490 0.02876 -0.0644 0.2167 1.0000
13.500 1.5495 0.03843 0.03218 -0.0623 0.1931 1.0000
13.750 1.5220 0.04328 0.03689 -0.0600 0.1632 1.0000
14.000 1.4903 0.04882 0.04231 -0.0579 0.1335 1.0000
14.250 1.4623 0.05431 0.04773 -0.0565 0.1082 1.0000
14.500 1.4375 0.05973 0.05311 -0.0555 0.0901 1.0000
14.750 1.4225 0.06425 0.05765 -0.0549 0.0799 1.0000
15.000 1.4075 0.06887 0.06230 -0.0545 0.0694 1.0000
15.250 1.3890 0.07406 0.06750 -0.0543 0.0559 1.0000
15.500 1.3642 0.08017 0.07358 -0.0543 0.0400 1.0000
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