GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il) Reynolds number: 500,000 Max Cl/Cd: 54.77 at α=-0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe229-il-500000.txt Download as CSV file: xf-goe229-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 229 (MVA H.39) 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.3027 0.08536 0.08288 -0.1029 0.9776 0.0201
-13.500 -0.3301 0.07495 0.07231 -0.1111 0.9708 0.0198
-13.250 -0.3553 0.06647 0.06365 -0.1181 0.9604 0.0197
-13.000 -0.3788 0.05968 0.05666 -0.1233 0.9478 0.0197
-12.750 -0.4001 0.05404 0.05079 -0.1272 0.9344 0.0197
-12.250 -0.4319 0.04486 0.04110 -0.1340 0.9086 0.0200
-12.000 -0.4409 0.04126 0.03723 -0.1377 0.8969 0.0201
-11.750 -0.4497 0.03691 0.03261 -0.1404 0.8868 0.0204
-11.500 -0.4437 0.03462 0.03022 -0.1417 0.8775 0.0207
-11.250 -0.4287 0.03290 0.02839 -0.1440 0.8700 0.0211
-11.000 -0.4103 0.03151 0.02693 -0.1461 0.8618 0.0214
-10.750 -0.3918 0.03018 0.02546 -0.1474 0.8550 0.0219
-10.500 -0.3731 0.02872 0.02386 -0.1486 0.8474 0.0225
-10.250 -0.3534 0.02722 0.02215 -0.1495 0.8408 0.0232
-10.000 -0.3320 0.02587 0.02059 -0.1504 0.8345 0.0240
-9.750 -0.3083 0.02520 0.01967 -0.1515 0.8275 0.0247
-9.500 -0.2879 0.02319 0.01760 -0.1513 0.8219 0.0257
-9.250 -0.2634 0.02246 0.01686 -0.1518 0.8150 0.0265
-9.000 -0.2384 0.02173 0.01608 -0.1521 0.8085 0.0273
-8.750 -0.2131 0.02095 0.01518 -0.1524 0.8026 0.0283
-8.500 -0.1873 0.02024 0.01437 -0.1527 0.7958 0.0292
-8.250 -0.1600 0.01981 0.01377 -0.1533 0.7899 0.0300
-8.000 -0.1377 0.01842 0.01240 -0.1529 0.7838 0.0313
-7.750 -0.1120 0.01775 0.01174 -0.1532 0.7773 0.0325
-7.500 -0.0853 0.01721 0.01112 -0.1536 0.7715 0.0336
-7.250 -0.0588 0.01664 0.01053 -0.1539 0.7647 0.0347
-7.000 -0.0316 0.01617 0.00998 -0.1542 0.7576 0.0358
-6.750 -0.0035 0.01591 0.00963 -0.1546 0.7496 0.0367
-6.500 0.0214 0.01480 0.00847 -0.1551 0.7411 0.0383
-6.250 0.0489 0.01420 0.00784 -0.1557 0.7326 0.0396
-6.000 0.0768 0.01375 0.00730 -0.1562 0.7241 0.0410
-5.750 0.1052 0.01335 0.00684 -0.1568 0.7158 0.0426
-5.500 0.1337 0.01302 0.00642 -0.1572 0.7081 0.0440
-5.250 0.1624 0.01269 0.00602 -0.1578 0.7004 0.0450
-5.000 0.1909 0.01219 0.00541 -0.1584 0.6913 0.0474
-4.750 0.2194 0.01187 0.00502 -0.1588 0.6809 0.0501
-4.500 0.2475 0.01167 0.00470 -0.1590 0.6701 0.0529
-4.250 0.2759 0.01146 0.00442 -0.1593 0.6591 0.0576
-4.000 0.3045 0.01089 0.00402 -0.1601 0.6489 0.1168
-3.750 0.3322 0.00975 0.00355 -0.1615 0.6378 0.3244
-3.500 0.3597 0.00981 0.00358 -0.1614 0.6229 0.3570
-3.250 0.3869 0.00994 0.00361 -0.1613 0.6068 0.3736
-3.000 0.4141 0.01005 0.00366 -0.1612 0.5920 0.3840
-2.750 0.4409 0.01023 0.00369 -0.1610 0.5755 0.3925
-2.500 0.4667 0.01042 0.00378 -0.1607 0.5574 0.4004
-2.250 0.4928 0.01065 0.00385 -0.1604 0.5405 0.4077
-2.000 0.5193 0.01078 0.00392 -0.1602 0.5260 0.4135
-1.750 0.5459 0.01095 0.00402 -0.1600 0.5125 0.4188
-1.500 0.5722 0.01117 0.00411 -0.1598 0.4981 0.4248
-1.250 0.5979 0.01133 0.00419 -0.1595 0.4822 0.4301
-1.000 0.6233 0.01155 0.00433 -0.1592 0.4644 0.4353
-0.750 0.6474 0.01182 0.00444 -0.1586 0.4405 0.4399
-0.500 0.6663 0.01239 0.00465 -0.1572 0.3818 0.4428
-0.250 0.6613 0.01440 0.00573 -0.1521 0.2102 0.4448
0.000 0.6781 0.01503 0.00613 -0.1505 0.1633 0.4476
0.250 0.6922 0.01580 0.00666 -0.1483 0.1062 0.4507
0.500 0.7148 0.01607 0.00689 -0.1476 0.1006 0.4547
0.750 0.7373 0.01627 0.00706 -0.1467 0.0981 0.4585
1.000 0.7589 0.01649 0.00723 -0.1458 0.0958 0.4611
1.250 0.7803 0.01666 0.00741 -0.1449 0.0934 0.4643
1.500 0.8016 0.01692 0.00766 -0.1440 0.0910 0.4673
1.750 0.8241 0.01718 0.00790 -0.1433 0.0894 0.4706
2.000 0.8472 0.01742 0.00814 -0.1428 0.0882 0.4738
2.250 0.8696 0.01772 0.00840 -0.1421 0.0853 0.4768
2.500 0.8909 0.01806 0.00869 -0.1414 0.0813 0.4797
2.750 0.9118 0.01840 0.00902 -0.1406 0.0670 0.4831
3.000 0.9301 0.01891 0.00948 -0.1394 0.0605 0.4865
3.250 0.9511 0.01928 0.00988 -0.1387 0.0589 0.4902
3.500 0.9709 0.01973 0.01033 -0.1378 0.0581 0.4937
3.750 0.9905 0.02018 0.01081 -0.1369 0.0577 0.4970
4.000 1.0098 0.02065 0.01133 -0.1360 0.0573 0.5007
4.250 1.0285 0.02117 0.01189 -0.1350 0.0570 0.5045
4.500 1.0468 0.02173 0.01249 -0.1341 0.0567 0.5086
4.750 1.0646 0.02235 0.01312 -0.1331 0.0565 0.5128
5.000 1.0821 0.02297 0.01381 -0.1321 0.0563 0.5173
5.250 1.0992 0.02364 0.01453 -0.1312 0.0562 0.5218
5.500 1.1157 0.02437 0.01530 -0.1301 0.0560 0.5266
5.750 1.1319 0.02514 0.01610 -0.1292 0.0559 0.5313
6.000 1.1478 0.02593 0.01697 -0.1282 0.0558 0.5363
6.250 1.1634 0.02678 0.01788 -0.1272 0.0557 0.5419
6.500 1.1785 0.02768 0.01883 -0.1262 0.0557 0.5477
6.750 1.1932 0.02861 0.01984 -0.1253 0.0556 0.5539
7.000 1.2067 0.02966 0.02097 -0.1243 0.0554 0.5611
7.250 1.2191 0.03082 0.02222 -0.1232 0.0549 0.5684
7.500 1.2321 0.03196 0.02345 -0.1222 0.0544 0.5766
7.750 1.2440 0.03321 0.02478 -0.1212 0.0539 0.5854
8.000 1.2551 0.03454 0.02621 -0.1202 0.0534 0.5951
8.250 1.2652 0.03599 0.02776 -0.1191 0.0529 0.6056
8.500 1.2734 0.03765 0.02951 -0.1180 0.0522 0.6175
8.750 1.2800 0.03948 0.03146 -0.1168 0.0515 0.6298
9.000 1.2847 0.04154 0.03364 -0.1156 0.0509 0.6430
9.250 1.2854 0.04404 0.03624 -0.1144 0.0503 0.6566
9.500 1.2817 0.04706 0.03939 -0.1130 0.0499 0.6702
9.750 1.2974 0.04819 0.04062 -0.1127 0.0491 0.6889
10.000 1.3080 0.04982 0.04237 -0.1121 0.0482 0.7089
10.500 1.3158 0.05372 0.04690 -0.1099 0.0465 1.0000
10.750 1.3177 0.05645 0.04969 -0.1092 0.0456 1.0000
11.000 1.3132 0.05993 0.05324 -0.1084 0.0448 1.0000
11.250 1.3100 0.06333 0.05672 -0.1077 0.0438 1.0000
11.500 1.3346 0.06355 0.05696 -0.1079 0.0418 1.0000
11.750 1.3467 0.06522 0.05867 -0.1077 0.0399 1.0000
12.000 1.3522 0.06766 0.06117 -0.1073 0.0385 1.0000
12.250 1.3743 0.06811 0.06164 -0.1074 0.0367 1.0000
12.500 1.3940 0.06886 0.06240 -0.1074 0.0344 1.0000
12.750 1.4141 0.06955 0.06306 -0.1074 0.0320 1.0000
13.000 1.4199 0.07193 0.06554 -0.1071 0.0281 1.0000
13.250 1.4374 0.07289 0.06626 -0.1072 0.0164 1.0000
13.500 1.4387 0.07581 0.06924 -0.1068 0.0154 1.0000
13.750 1.4396 0.07885 0.07235 -0.1066 0.0147 1.0000
14.000 1.4406 0.08188 0.07544 -0.1063 0.0142 1.0000
14.250 1.4415 0.08496 0.07859 -0.1062 0.0137 1.0000
14.500 1.4420 0.08811 0.08182 -0.1060 0.0134 1.0000
14.750 1.4426 0.09125 0.08504 -0.1060 0.0132 1.0000
15.000 1.4418 0.09462 0.08849 -0.1060 0.0130 1.0000
15.250 1.4409 0.09802 0.09197 -0.1060 0.0128 1.0000
15.500 1.4383 0.10170 0.09574 -0.1062 0.0126 1.0000
15.750 1.4353 0.10546 0.09959 -0.1065 0.0123 1.0000
16.000 1.4315 0.10935 0.10357 -0.1069 0.0121 1.0000
16.250 1.4258 0.11356 0.10788 -0.1074 0.0119 1.0000
16.500 1.4198 0.11788 0.11230 -0.1080 0.0118 1.0000
16.750 1.4117 0.12258 0.11710 -0.1089 0.0116 1.0000
17.000 1.4020 0.12761 0.12223 -0.1100 0.0114 1.0000
17.250 1.3912 0.13290 0.12763 -0.1114 0.0113 1.0000
17.500 1.3789 0.13850 0.13334 -0.1130 0.0112 1.0000
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