GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.47 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe164-il-1000000.txt Download as CSV file: xf-goe164-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3296 0.13049 0.12885 -0.0208 1.0000 0.0101
-10.750 -0.3277 0.12736 0.12573 -0.0214 1.0000 0.0102
-10.500 -0.3256 0.12435 0.12273 -0.0218 1.0000 0.0102
-10.250 -0.3231 0.12143 0.11983 -0.0220 1.0000 0.0103
-10.000 -0.3208 0.11852 0.11693 -0.0221 1.0000 0.0103
-9.750 -0.3142 0.11505 0.11348 -0.0237 0.9997 0.0103
-9.500 -0.3005 0.11072 0.10914 -0.0274 0.9986 0.0103
-9.250 -0.2891 0.10633 0.10475 -0.0302 0.9976 0.0106
-9.000 -0.2722 0.10308 0.10150 -0.0335 0.9965 0.0108
-8.750 -0.2556 0.09973 0.09815 -0.0370 0.9955 0.0110
-8.500 -0.2389 0.09627 0.09469 -0.0408 0.9946 0.0114
-8.250 -0.2251 0.09277 0.09119 -0.0440 0.9926 0.0120
-7.000 -0.1055 0.01619 0.01285 -0.1441 0.9679 0.0109
-6.750 -0.0717 0.01509 0.01162 -0.1459 0.9648 0.0114
-6.500 -0.0338 0.01400 0.01037 -0.1484 0.9626 0.0119
-6.250 0.0040 0.01295 0.00914 -0.1509 0.9608 0.0124
-6.000 0.0408 0.01196 0.00799 -0.1529 0.9589 0.0129
-5.750 0.0629 0.01132 0.00724 -0.1516 0.9501 0.0133
-5.500 0.0973 0.01057 0.00635 -0.1529 0.9444 0.0137
-5.250 0.1264 0.00954 0.00517 -0.1532 0.9304 0.0149
-5.000 0.1638 0.00916 0.00469 -0.1550 0.8992 0.0161
-4.750 0.1960 0.00906 0.00420 -0.1556 0.8290 0.0172
-4.500 0.2211 0.00902 0.00391 -0.1547 0.7958 0.0178
-4.250 0.2471 0.00859 0.00330 -0.1543 0.7734 0.0197
-4.000 0.2736 0.00850 0.00310 -0.1538 0.7559 0.0213
-3.500 0.3278 0.00817 0.00258 -0.1531 0.7263 0.0263
-3.250 0.3551 0.00811 0.00244 -0.1528 0.7132 0.0290
-3.000 0.3826 0.00790 0.00215 -0.1526 0.7004 0.0335
-2.750 0.4099 0.00784 0.00202 -0.1523 0.6874 0.0374
-2.500 0.4372 0.00770 0.00181 -0.1520 0.6737 0.0437
-2.250 0.4644 0.00765 0.00168 -0.1516 0.6585 0.0490
-2.000 0.4913 0.00737 0.00148 -0.1514 0.6405 0.0993
-1.750 0.5177 0.00739 0.00151 -0.1510 0.6184 0.1378
-1.500 0.5441 0.00751 0.00154 -0.1506 0.5925 0.1487
-1.250 0.5704 0.00769 0.00158 -0.1501 0.5669 0.1554
-1.000 0.5970 0.00780 0.00160 -0.1497 0.5455 0.1617
-0.750 0.6238 0.00792 0.00164 -0.1493 0.5272 0.1660
-0.500 0.6507 0.00806 0.00167 -0.1489 0.5097 0.1697
-0.250 0.6776 0.00814 0.00168 -0.1486 0.4912 0.1738
0.000 0.7042 0.00827 0.00173 -0.1483 0.4695 0.1784
0.250 0.7302 0.00850 0.00182 -0.1478 0.4393 0.1835
0.500 0.7556 0.00878 0.00190 -0.1473 0.4000 0.1858
0.750 0.7814 0.00897 0.00196 -0.1468 0.3707 0.1900
1.000 0.8076 0.00914 0.00205 -0.1464 0.3519 0.1935
1.250 0.8342 0.00928 0.00213 -0.1461 0.3396 0.1972
1.500 0.8609 0.00943 0.00221 -0.1458 0.3296 0.2000
1.750 0.8876 0.00952 0.00228 -0.1455 0.3204 0.2049
2.000 0.9146 0.00961 0.00236 -0.1453 0.3140 0.2094
2.250 0.9414 0.00972 0.00245 -0.1450 0.3073 0.2135
2.500 0.9682 0.00981 0.00254 -0.1447 0.3011 0.2189
2.750 0.9951 0.00989 0.00264 -0.1445 0.2948 0.2253
3.000 1.0215 0.01003 0.00275 -0.1442 0.2874 0.2330
3.250 1.0485 0.01010 0.00286 -0.1439 0.2809 0.2436
3.500 1.0748 0.01022 0.00299 -0.1436 0.2726 0.2623
3.750 1.1013 0.01028 0.00316 -0.1434 0.2624 0.3241
4.000 1.1273 0.01039 0.00334 -0.1431 0.2483 0.3956
4.750 1.1944 0.01062 0.00424 -0.1403 0.1740 1.0000
5.000 1.2198 0.01085 0.00444 -0.1398 0.1695 1.0000
5.250 1.2450 0.01110 0.00467 -0.1393 0.1652 1.0000
5.500 1.2701 0.01134 0.00490 -0.1388 0.1598 1.0000
5.750 1.2952 0.01158 0.00512 -0.1383 0.1547 1.0000
6.000 1.3197 0.01186 0.00537 -0.1377 0.1494 1.0000
6.250 1.3447 0.01208 0.00561 -0.1372 0.1454 1.0000
6.500 1.3698 0.01229 0.00582 -0.1367 0.1404 1.0000
6.750 1.3935 0.01262 0.00609 -0.1360 0.1300 1.0000
7.000 1.4116 0.01346 0.00666 -0.1345 0.0866 1.0000
7.250 1.4340 0.01388 0.00707 -0.1336 0.0824 1.0000
7.500 1.4560 0.01432 0.00751 -0.1326 0.0773 1.0000
7.750 1.4792 0.01463 0.00786 -0.1318 0.0737 1.0000
8.000 1.5015 0.01501 0.00827 -0.1309 0.0689 1.0000
8.250 1.5226 0.01547 0.00871 -0.1298 0.0585 1.0000
8.500 1.5323 0.01687 0.00982 -0.1268 0.0182 1.0000
8.750 1.5505 0.01752 0.01050 -0.1251 0.0149 1.0000
9.000 1.5695 0.01805 0.01107 -0.1237 0.0135 1.0000
9.250 1.5862 0.01872 0.01179 -0.1218 0.0122 1.0000
9.500 1.5994 0.01952 0.01268 -0.1193 0.0111 1.0000
9.750 1.6148 0.02008 0.01329 -0.1173 0.0106 1.0000
10.000 1.6288 0.02072 0.01399 -0.1150 0.0101 1.0000
10.250 1.6412 0.02144 0.01477 -0.1126 0.0096 1.0000
10.500 1.6524 0.02223 0.01562 -0.1100 0.0091 1.0000
10.750 1.6598 0.02328 0.01675 -0.1069 0.0086 1.0000
11.000 1.6583 0.02492 0.01853 -0.1028 0.0081 1.0000
11.250 1.6702 0.02571 0.01938 -0.1007 0.0079 1.0000
11.500 1.6784 0.02678 0.02053 -0.0982 0.0076 1.0000
11.750 1.6851 0.02800 0.02184 -0.0957 0.0074 1.0000
12.000 1.6904 0.02939 0.02331 -0.0933 0.0071 1.0000
12.250 1.6944 0.03096 0.02497 -0.0910 0.0069 1.0000
12.500 1.6977 0.03270 0.02679 -0.0889 0.0067 1.0000
12.750 1.6994 0.03472 0.02891 -0.0870 0.0065 1.0000
13.000 1.6997 0.03701 0.03129 -0.0854 0.0063 1.0000
13.250 1.6971 0.03979 0.03417 -0.0841 0.0062 1.0000
13.500 1.6910 0.04313 0.03762 -0.0830 0.0060 1.0000
13.750 1.6795 0.04727 0.04190 -0.0822 0.0059 1.0000
14.000 1.6632 0.05226 0.04703 -0.0818 0.0058 1.0000
14.250 1.6449 0.05772 0.05265 -0.0818 0.0057 1.0000
14.500 1.6267 0.06341 0.05848 -0.0822 0.0057 1.0000
14.750 1.6209 0.06758 0.06276 -0.0827 0.0056 1.0000
15.000 1.6131 0.07210 0.06739 -0.0833 0.0056 1.0000
15.250 1.6033 0.07700 0.07240 -0.0841 0.0056 1.0000
15.500 1.5945 0.08189 0.07740 -0.0850 0.0055 1.0000
15.750 1.5849 0.08693 0.08255 -0.0861 0.0055 1.0000
16.000 1.5753 0.09202 0.08774 -0.0873 0.0054 1.0000
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