GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.11 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe164-il-1000000-n5.txt Download as CSV file: xf-goe164-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 164 (MVA MK.10) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1820 0.10301 0.10129 -0.0593 0.9873 0.0049
-9.500 -0.1693 0.09970 0.09798 -0.0620 0.9858 0.0050
-8.500 -0.2096 0.03102 0.02873 -0.1386 0.9585 0.0050
-8.000 -0.1413 0.01653 0.01335 -0.1574 0.9460 0.0052
-7.750 -0.1076 0.01497 0.01156 -0.1598 0.9396 0.0053
-7.250 -0.0422 0.01279 0.00898 -0.1630 0.9050 0.0057
-7.000 -0.0099 0.01216 0.00791 -0.1642 0.8388 0.0060
-6.750 0.0148 0.01180 0.00725 -0.1636 0.8045 0.0062
-6.500 0.0406 0.01147 0.00671 -0.1632 0.7827 0.0065
-6.250 0.0671 0.01096 0.00600 -0.1631 0.7663 0.0068
-6.000 0.0941 0.01047 0.00535 -0.1630 0.7530 0.0072
-5.750 0.1213 0.01016 0.00492 -0.1628 0.7409 0.0076
-5.500 0.1482 0.00990 0.00453 -0.1626 0.7260 0.0081
-5.250 0.1749 0.00969 0.00417 -0.1622 0.7076 0.0086
-5.000 0.2016 0.00951 0.00383 -0.1619 0.6879 0.0090
-4.750 0.2286 0.00934 0.00352 -0.1616 0.6705 0.0095
-4.500 0.2558 0.00910 0.00316 -0.1614 0.6526 0.0107
-4.250 0.2830 0.00898 0.00294 -0.1611 0.6355 0.0120
-4.000 0.3102 0.00889 0.00273 -0.1609 0.6177 0.0131
-3.750 0.3373 0.00878 0.00249 -0.1606 0.5977 0.0153
-3.500 0.3641 0.00874 0.00234 -0.1602 0.5750 0.0179
-3.250 0.3911 0.00870 0.00222 -0.1600 0.5552 0.0225
-3.000 0.4184 0.00870 0.00212 -0.1597 0.5391 0.0262
-2.750 0.4455 0.00868 0.00202 -0.1595 0.5210 0.0305
-2.500 0.4722 0.00873 0.00195 -0.1591 0.4964 0.0345
-2.250 0.4987 0.00882 0.00189 -0.1588 0.4691 0.0381
-2.000 0.5254 0.00887 0.00183 -0.1584 0.4422 0.0446
-1.750 0.5516 0.00900 0.00180 -0.1581 0.4077 0.0534
-1.500 0.5775 0.00898 0.00178 -0.1578 0.3714 0.1075
-1.250 0.6038 0.00913 0.00184 -0.1574 0.3471 0.1270
-1.000 0.6306 0.00926 0.00189 -0.1571 0.3305 0.1364
-0.750 0.6575 0.00938 0.00193 -0.1568 0.3176 0.1426
-0.500 0.6846 0.00948 0.00197 -0.1566 0.3088 0.1465
-0.250 0.7119 0.00954 0.00201 -0.1564 0.3029 0.1514
0.000 0.7392 0.00962 0.00205 -0.1562 0.2965 0.1564
0.250 0.7663 0.00971 0.00212 -0.1559 0.2904 0.1626
0.500 0.7936 0.00978 0.00218 -0.1557 0.2848 0.1684
0.750 0.8205 0.00989 0.00224 -0.1555 0.2768 0.1710
1.000 0.8474 0.01000 0.00230 -0.1552 0.2680 0.1732
1.250 0.8740 0.01013 0.00237 -0.1549 0.2568 0.1758
1.500 0.9002 0.01030 0.00247 -0.1546 0.2409 0.1798
1.750 0.9223 0.01090 0.00277 -0.1536 0.1793 0.1830
2.000 0.9481 0.01112 0.00292 -0.1531 0.1684 0.1860
2.250 0.9744 0.01127 0.00305 -0.1528 0.1631 0.1885
2.500 1.0008 0.01139 0.00318 -0.1525 0.1598 0.1920
2.750 1.0269 0.01155 0.00333 -0.1521 0.1556 0.1960
3.000 1.0530 0.01170 0.00347 -0.1518 0.1525 0.2001
3.500 1.1056 0.01194 0.00375 -0.1511 0.1487 0.2103
3.750 1.1319 0.01206 0.00389 -0.1508 0.1472 0.2159
4.000 1.1579 0.01219 0.00405 -0.1505 0.1452 0.2225
4.250 1.1838 0.01234 0.00422 -0.1501 0.1426 0.2316
4.500 1.2093 0.01250 0.00441 -0.1497 0.1394 0.2459
4.750 1.2347 0.01266 0.00463 -0.1493 0.1358 0.2813
5.000 1.2606 0.01275 0.00486 -0.1491 0.1338 0.3477
5.250 1.2860 0.01290 0.00507 -0.1487 0.1300 0.3849
5.500 1.3104 0.01312 0.00533 -0.1482 0.1203 0.4328
6.000 1.3509 0.01323 0.00620 -0.1456 0.0828 1.0000
6.250 1.3745 0.01354 0.00651 -0.1449 0.0783 1.0000
6.500 1.3981 0.01385 0.00683 -0.1442 0.0759 1.0000
6.750 1.4211 0.01419 0.00718 -0.1433 0.0733 1.0000
7.000 1.4439 0.01454 0.00755 -0.1425 0.0702 1.0000
7.250 1.4674 0.01480 0.00783 -0.1418 0.0687 1.0000
7.500 1.4908 0.01505 0.00812 -0.1411 0.0663 1.0000
7.750 1.5116 0.01552 0.00853 -0.1399 0.0560 1.0000
8.000 1.5229 0.01673 0.00951 -0.1372 0.0153 1.0000
8.250 1.5422 0.01724 0.01003 -0.1358 0.0113 1.0000
8.500 1.5615 0.01773 0.01054 -0.1344 0.0096 1.0000
8.750 1.5792 0.01826 0.01110 -0.1327 0.0079 1.0000
9.000 1.5963 0.01874 0.01161 -0.1309 0.0071 1.0000
9.250 1.6120 0.01928 0.01219 -0.1289 0.0064 1.0000
9.500 1.6263 0.01991 0.01285 -0.1267 0.0056 1.0000
9.750 1.6413 0.02048 0.01348 -0.1247 0.0053 1.0000
10.000 1.6554 0.02110 0.01415 -0.1225 0.0049 1.0000
10.250 1.6687 0.02177 0.01487 -0.1203 0.0045 1.0000
10.500 1.6805 0.02253 0.01568 -0.1179 0.0042 1.0000
10.750 1.6905 0.02343 0.01663 -0.1154 0.0038 1.0000
11.000 1.7019 0.02424 0.01751 -0.1131 0.0037 1.0000
11.250 1.7119 0.02517 0.01851 -0.1108 0.0035 1.0000
11.500 1.7212 0.02617 0.01958 -0.1084 0.0033 1.0000
11.750 1.7296 0.02727 0.02077 -0.1061 0.0032 1.0000
12.000 1.7371 0.02848 0.02204 -0.1039 0.0030 1.0000
12.250 1.7432 0.02984 0.02348 -0.1016 0.0029 1.0000
12.500 1.7477 0.03142 0.02514 -0.0995 0.0027 1.0000
12.750 1.7500 0.03328 0.02709 -0.0973 0.0026 1.0000
13.000 1.7491 0.03557 0.02949 -0.0953 0.0025 1.0000
13.250 1.7513 0.03771 0.03172 -0.0938 0.0025 1.0000
13.500 1.7526 0.04005 0.03417 -0.0925 0.0024 1.0000
13.750 1.7521 0.04268 0.03690 -0.0914 0.0024 1.0000
14.000 1.7508 0.04551 0.03984 -0.0904 0.0023 1.0000
14.250 1.7477 0.04867 0.04311 -0.0897 0.0023 1.0000
14.500 1.7432 0.05210 0.04666 -0.0892 0.0022 1.0000
14.750 1.7377 0.05578 0.05046 -0.0888 0.0021 1.0000
15.000 1.7311 0.05974 0.05453 -0.0888 0.0021 1.0000
15.250 1.7233 0.06398 0.05889 -0.0889 0.0020 1.0000
15.500 1.7142 0.06851 0.06354 -0.0893 0.0020 1.0000
15.750 1.7032 0.07347 0.06861 -0.0899 0.0020 1.0000
16.000 1.6906 0.07880 0.07407 -0.0908 0.0019 1.0000
16.250 1.6783 0.08414 0.07953 -0.0918 0.0019 1.0000
16.500 1.6643 0.08985 0.08536 -0.0930 0.0019 1.0000
16.750 1.6489 0.09591 0.09154 -0.0945 0.0019 1.0000
17.000 1.6360 0.10165 0.09739 -0.0960 0.0018 1.0000
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Polar data table (+)
Polar graphs
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