GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il) Reynolds number: 1,000,000 Max Cl/Cd: 59.55 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe229-il-1000000.txt Download as CSV file: xf-goe229-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.5881 0.09432 0.09206 -0.0827 1.0000 0.0119
-16.750 -0.6172 0.08609 0.08368 -0.0871 1.0000 0.0120
-16.500 -0.6376 0.07992 0.07739 -0.0900 1.0000 0.0120
-16.250 -0.6535 0.07492 0.07229 -0.0921 0.9998 0.0121
-16.000 -0.6562 0.06944 0.06669 -0.0970 0.9975 0.0122
-15.750 -0.6552 0.06457 0.06170 -0.1018 0.9950 0.0124
-15.500 -0.6516 0.06028 0.05729 -0.1061 0.9906 0.0126
-15.250 -0.6454 0.05642 0.05333 -0.1101 0.9841 0.0127
-15.000 -0.6386 0.05308 0.04989 -0.1133 0.9743 0.0128
-14.750 -0.6338 0.05017 0.04686 -0.1155 0.9609 0.0129
-14.500 -0.6346 0.04728 0.04384 -0.1167 0.9460 0.0131
-14.250 -0.6423 0.04406 0.04046 -0.1175 0.9316 0.0134
-14.000 -0.6410 0.04169 0.03799 -0.1183 0.9193 0.0136
-13.750 -0.6361 0.03956 0.03577 -0.1194 0.9079 0.0138
-13.500 -0.6281 0.03765 0.03379 -0.1205 0.8975 0.0140
-13.250 -0.6194 0.03582 0.03187 -0.1216 0.8875 0.0142
-13.000 -0.6089 0.03403 0.03002 -0.1230 0.8782 0.0144
-12.750 -0.5976 0.03235 0.02826 -0.1242 0.8699 0.0146
-12.500 -0.5848 0.03071 0.02655 -0.1256 0.8615 0.0149
-12.250 -0.5716 0.02912 0.02486 -0.1269 0.8534 0.0152
-12.000 -0.5569 0.02759 0.02325 -0.1284 0.8451 0.0156
-11.750 -0.5418 0.02619 0.02174 -0.1300 0.8373 0.0159
-11.500 -0.5203 0.02486 0.02033 -0.1323 0.8301 0.0162
-11.250 -0.5031 0.02295 0.01830 -0.1349 0.8226 0.0167
-11.000 -0.4785 0.02155 0.01686 -0.1378 0.8159 0.0172
-10.750 -0.4507 0.02049 0.01575 -0.1406 0.8089 0.0176
-10.500 -0.4220 0.01958 0.01476 -0.1432 0.8024 0.0180
-10.250 -0.3940 0.01881 0.01392 -0.1451 0.7954 0.0186
-10.000 -0.3671 0.01819 0.01320 -0.1463 0.7887 0.0192
-9.750 -0.3394 0.01764 0.01258 -0.1474 0.7826 0.0197
-9.500 -0.3113 0.01724 0.01210 -0.1483 0.7761 0.0201
-9.250 -0.2870 0.01616 0.01095 -0.1494 0.7701 0.0210
-9.000 -0.2588 0.01575 0.01054 -0.1503 0.7640 0.0216
-8.750 -0.2308 0.01543 0.01016 -0.1510 0.7578 0.0223
-8.500 -0.2026 0.01505 0.00973 -0.1517 0.7519 0.0231
-8.250 -0.1744 0.01468 0.00930 -0.1523 0.7452 0.0238
-8.000 -0.1464 0.01441 0.00895 -0.1528 0.7369 0.0244
-7.750 -0.1191 0.01379 0.00826 -0.1535 0.7280 0.0252
-7.500 -0.0918 0.01319 0.00761 -0.1542 0.7199 0.0262
-7.250 -0.0631 0.01288 0.00727 -0.1548 0.7127 0.0271
-7.000 -0.0348 0.01259 0.00692 -0.1553 0.7057 0.0280
-6.750 -0.0058 0.01227 0.00657 -0.1559 0.6990 0.0289
-6.500 0.0228 0.01206 0.00629 -0.1563 0.6913 0.0296
-6.250 0.0518 0.01194 0.00613 -0.1567 0.6841 0.0302
-6.000 0.0800 0.01120 0.00528 -0.1576 0.6751 0.0317
-5.750 0.1087 0.01091 0.00493 -0.1581 0.6640 0.0328
-5.500 0.1369 0.01071 0.00465 -0.1585 0.6504 0.0339
-5.250 0.1650 0.01057 0.00442 -0.1587 0.6363 0.0351
-5.000 0.1932 0.01045 0.00420 -0.1590 0.6227 0.0360
-4.750 0.2216 0.01035 0.00402 -0.1592 0.6085 0.0367
-4.500 0.2492 0.01018 0.00371 -0.1594 0.5898 0.0385
-4.250 0.2766 0.01010 0.00352 -0.1596 0.5697 0.0408
-4.000 0.3042 0.01007 0.00338 -0.1597 0.5529 0.0428
-3.750 0.3318 0.01007 0.00328 -0.1598 0.5379 0.0447
-3.500 0.3593 0.01003 0.00315 -0.1599 0.5212 0.0526
-3.250 0.3871 0.00901 0.00266 -0.1612 0.5037 0.2405
-3.000 0.4147 0.00876 0.00261 -0.1616 0.4896 0.3279
-2.750 0.4425 0.00882 0.00266 -0.1617 0.4750 0.3492
-2.500 0.4695 0.00899 0.00272 -0.1617 0.4562 0.3606
-2.250 0.4952 0.00923 0.00282 -0.1614 0.4254 0.3707
-2.000 0.5020 0.01080 0.00353 -0.1580 0.2579 0.3754
-1.750 0.5205 0.01153 0.00394 -0.1566 0.1867 0.3816
-1.500 0.5392 0.01226 0.00436 -0.1552 0.1080 0.3879
-1.250 0.5655 0.01245 0.00449 -0.1550 0.0995 0.3936
-1.000 0.5921 0.01260 0.00463 -0.1549 0.0958 0.3997
-0.750 0.6181 0.01279 0.00477 -0.1547 0.0911 0.4043
-0.500 0.6445 0.01295 0.00489 -0.1545 0.0882 0.4079
-0.250 0.6699 0.01314 0.00503 -0.1543 0.0817 0.4134
0.000 0.6934 0.01344 0.00525 -0.1537 0.0591 0.4180
0.250 0.7187 0.01363 0.00542 -0.1533 0.0561 0.4209
0.500 0.7440 0.01381 0.00557 -0.1530 0.0548 0.4235
0.750 0.7689 0.01400 0.00574 -0.1526 0.0539 0.4257
1.000 0.7935 0.01417 0.00592 -0.1522 0.0531 0.4291
1.250 0.8172 0.01437 0.00614 -0.1516 0.0522 0.4325
1.500 0.8389 0.01459 0.00637 -0.1507 0.0512 0.4360
1.750 0.8592 0.01484 0.00664 -0.1494 0.0501 0.4395
2.000 0.8807 0.01510 0.00689 -0.1485 0.0496 0.4421
2.250 0.9030 0.01537 0.00716 -0.1477 0.0492 0.4445
2.500 0.9255 0.01564 0.00745 -0.1470 0.0489 0.4480
2.750 0.9474 0.01594 0.00778 -0.1463 0.0487 0.4510
3.000 0.9689 0.01627 0.00813 -0.1455 0.0484 0.4540
3.250 0.9898 0.01663 0.00850 -0.1446 0.0482 0.4570
3.500 1.0101 0.01702 0.00889 -0.1436 0.0480 0.4598
3.750 1.0303 0.01743 0.00931 -0.1427 0.0478 0.4630
4.000 1.0501 0.01785 0.00976 -0.1418 0.0477 0.4666
4.250 1.0694 0.01830 0.01025 -0.1408 0.0475 0.4700
4.500 1.0881 0.01880 0.01077 -0.1398 0.0473 0.4734
4.750 1.1062 0.01935 0.01133 -0.1387 0.0472 0.4765
5.000 1.1239 0.01994 0.01194 -0.1376 0.0471 0.4796
5.250 1.1412 0.02055 0.01260 -0.1365 0.0469 0.4841
5.500 1.1580 0.02122 0.01331 -0.1354 0.0468 0.4883
5.750 1.1740 0.02195 0.01407 -0.1342 0.0466 0.4924
6.000 1.1891 0.02277 0.01491 -0.1330 0.0460 0.4958
6.250 1.2027 0.02370 0.01590 -0.1317 0.0454 0.5004
6.500 1.2116 0.02498 0.01726 -0.1299 0.0446 0.5048
6.750 1.2164 0.02659 0.01895 -0.1278 0.0441 0.5089
7.000 1.2365 0.02714 0.01951 -0.1274 0.0438 0.5136
7.250 1.2525 0.02799 0.02042 -0.1265 0.0434 0.5195
7.500 1.2670 0.02897 0.02145 -0.1256 0.0431 0.5254
7.750 1.2818 0.02996 0.02247 -0.1247 0.0426 0.5315
8.000 1.2967 0.03096 0.02353 -0.1240 0.0417 0.5393
8.250 1.3105 0.03204 0.02466 -0.1231 0.0409 0.5473
8.500 1.3234 0.03322 0.02590 -0.1222 0.0402 0.5565
8.750 1.3359 0.03445 0.02720 -0.1214 0.0395 0.5666
9.000 1.3459 0.03594 0.02876 -0.1204 0.0389 0.5785
9.250 1.3457 0.03836 0.03130 -0.1188 0.0381 0.5899
9.500 1.3728 0.03839 0.03134 -0.1191 0.0374 0.6084
9.750 1.3957 0.03878 0.03177 -0.1192 0.0359 0.6270
10.000 1.4214 0.03891 0.03189 -0.1194 0.0338 0.6461
10.250 1.4431 0.03942 0.03238 -0.1195 0.0318 0.6636
10.500 1.4622 0.04014 0.03310 -0.1193 0.0258 0.6801
10.750 1.4669 0.04220 0.03512 -0.1182 0.0137 0.6942
11.000 1.4733 0.04416 0.03719 -0.1173 0.0128 0.7107
11.250 1.4791 0.04621 0.03937 -0.1164 0.0121 0.7347
11.500 1.4825 0.04791 0.04156 -0.1150 0.0114 1.0000
11.750 1.4879 0.05007 0.04377 -0.1142 0.0110 1.0000
12.000 1.4941 0.05219 0.04594 -0.1135 0.0107 1.0000
12.250 1.4990 0.05449 0.04829 -0.1128 0.0105 1.0000
12.500 1.5033 0.05688 0.05073 -0.1121 0.0102 1.0000
12.750 1.5067 0.05937 0.05328 -0.1114 0.0099 1.0000
13.000 1.5085 0.06207 0.05604 -0.1108 0.0096 1.0000
13.250 1.5090 0.06497 0.05900 -0.1102 0.0094 1.0000
13.500 1.5084 0.06804 0.06214 -0.1096 0.0091 1.0000
13.750 1.5044 0.07156 0.06575 -0.1090 0.0089 1.0000
14.000 1.5035 0.07473 0.06900 -0.1086 0.0087 1.0000
14.250 1.5046 0.07769 0.07202 -0.1083 0.0086 1.0000
14.500 1.5054 0.08070 0.07510 -0.1080 0.0084 1.0000
14.750 1.5043 0.08401 0.07848 -0.1078 0.0082 1.0000
15.000 1.5032 0.08733 0.08187 -0.1077 0.0081 1.0000
15.250 1.5009 0.09081 0.08542 -0.1076 0.0079 1.0000
15.500 1.4971 0.09453 0.08922 -0.1076 0.0078 1.0000
15.750 1.4940 0.09819 0.09296 -0.1076 0.0076 1.0000
16.000 1.4893 0.10212 0.09697 -0.1078 0.0075 1.0000
16.250 1.4838 0.10620 0.10113 -0.1081 0.0074 1.0000
16.500 1.4784 0.11027 0.10528 -0.1085 0.0073 1.0000
16.750 1.4703 0.11478 0.10988 -0.1091 0.0072 1.0000
17.000 1.4615 0.11949 0.11468 -0.1098 0.0071 1.0000
17.250 1.4509 0.12455 0.11983 -0.1108 0.0070 1.0000
17.500 1.4383 0.13001 0.12539 -0.1120 0.0069 1.0000
17.750 1.4233 0.13591 0.13141 -0.1136 0.0069 1.0000
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