GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 500,000 Max Cl/Cd: 97 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe190-il-500000-n5.txt Download as CSV file: xf-goe190-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 190 (MVA MK.18) 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6616 0.07165 0.06876 -0.0717 0.9947 0.0175
-13.250 -0.6863 0.06322 0.06017 -0.0787 0.9928 0.0174
-13.000 -0.6927 0.05802 0.05487 -0.0833 0.9903 0.0178
-12.750 -0.6987 0.05291 0.04965 -0.0884 0.9874 0.0181
-12.500 -0.7007 0.04838 0.04501 -0.0937 0.9847 0.0184
-12.250 -0.7065 0.04429 0.04081 -0.0976 0.9800 0.0187
-12.000 -0.6962 0.04010 0.03648 -0.1041 0.9759 0.0192
-11.750 -0.6748 0.03609 0.03232 -0.1121 0.9735 0.0197
-11.500 -0.6464 0.03291 0.02905 -0.1193 0.9721 0.0203
-11.250 -0.6314 0.03064 0.02671 -0.1219 0.9683 0.0208
-11.000 -0.6063 0.02848 0.02445 -0.1258 0.9654 0.0216
-10.750 -0.5762 0.02639 0.02221 -0.1301 0.9633 0.0224
-10.500 -0.5423 0.02452 0.02015 -0.1345 0.9616 0.0233
-10.250 -0.5059 0.02279 0.01832 -0.1390 0.9602 0.0241
-10.000 -0.4682 0.02146 0.01692 -0.1429 0.9591 0.0249
-9.750 -0.4384 0.02049 0.01586 -0.1447 0.9570 0.0257
-9.500 -0.4193 0.01971 0.01500 -0.1440 0.9522 0.0265
-9.250 -0.3888 0.01891 0.01408 -0.1453 0.9497 0.0274
-9.000 -0.3554 0.01816 0.01319 -0.1472 0.9477 0.0282
-8.750 -0.3199 0.01727 0.01227 -0.1495 0.9459 0.0291
-8.500 -0.2833 0.01669 0.01165 -0.1517 0.9443 0.0301
-8.250 -0.2649 0.01625 0.01116 -0.1501 0.9386 0.0308
-8.000 -0.2388 0.01574 0.01058 -0.1500 0.9339 0.0317
-7.750 -0.2065 0.01519 0.00994 -0.1511 0.9304 0.0326
-7.500 -0.1820 0.01475 0.00942 -0.1505 0.9244 0.0333
-7.250 -0.1612 0.01419 0.00882 -0.1492 0.9157 0.0340
-7.000 -0.1440 0.01372 0.00832 -0.1471 0.9026 0.0348
-6.500 -0.0691 0.01268 0.00715 -0.1510 0.8696 0.0369
-6.250 -0.0184 0.01213 0.00640 -0.1556 0.8381 0.0381
-6.000 0.0156 0.01191 0.00590 -0.1567 0.8004 0.0392
-5.750 0.0420 0.01180 0.00559 -0.1563 0.7757 0.0399
-5.250 0.0927 0.01128 0.00483 -0.1553 0.7443 0.0422
-5.000 0.1186 0.01112 0.00457 -0.1548 0.7322 0.0434
-4.750 0.1446 0.01098 0.00433 -0.1543 0.7214 0.0447
-4.500 0.1711 0.01082 0.00410 -0.1539 0.7115 0.0462
-4.250 0.1974 0.01073 0.00391 -0.1534 0.7016 0.0476
-4.000 0.2235 0.01052 0.00362 -0.1529 0.6907 0.0497
-3.750 0.2497 0.01036 0.00341 -0.1525 0.6797 0.0521
-3.500 0.2757 0.01026 0.00322 -0.1519 0.6666 0.0545
-3.250 0.3011 0.01020 0.00306 -0.1512 0.6477 0.0569
-3.000 0.3256 0.01013 0.00287 -0.1503 0.6228 0.0610
-2.750 0.3496 0.01011 0.00271 -0.1494 0.5937 0.0665
-2.500 0.3739 0.01009 0.00257 -0.1485 0.5723 0.0764
-2.000 0.4232 0.00947 0.00226 -0.1474 0.5456 0.2309
-1.750 0.4493 0.00952 0.00230 -0.1469 0.5369 0.2557
-1.500 0.4759 0.00958 0.00233 -0.1464 0.5287 0.2684
-1.250 0.5022 0.00968 0.00235 -0.1459 0.5216 0.2770
-1.000 0.5292 0.00973 0.00240 -0.1455 0.5159 0.2854
-0.750 0.5561 0.00982 0.00244 -0.1450 0.5105 0.2933
-0.250 0.6096 0.00996 0.00255 -0.1442 0.5006 0.3049
0.000 0.6365 0.01003 0.00257 -0.1438 0.4955 0.3089
0.250 0.6629 0.01010 0.00265 -0.1433 0.4904 0.3145
0.500 0.6895 0.01019 0.00272 -0.1428 0.4862 0.3194
0.750 0.7166 0.01023 0.00276 -0.1425 0.4820 0.3220
1.000 0.7433 0.01029 0.00280 -0.1420 0.4772 0.3243
1.250 0.7695 0.01037 0.00285 -0.1415 0.4722 0.3266
1.500 0.7959 0.01043 0.00292 -0.1411 0.4675 0.3292
1.750 0.8226 0.01048 0.00299 -0.1406 0.4625 0.3320
2.000 0.8488 0.01055 0.00307 -0.1401 0.4575 0.3353
2.250 0.8745 0.01066 0.00315 -0.1395 0.4528 0.3386
2.500 0.9011 0.01071 0.00322 -0.1391 0.4470 0.3416
2.750 0.9266 0.01080 0.00330 -0.1385 0.4393 0.3444
3.000 0.9521 0.01089 0.00340 -0.1379 0.4315 0.3475
3.250 0.9773 0.01099 0.00350 -0.1372 0.4229 0.3509
3.500 1.0026 0.01109 0.00362 -0.1365 0.4158 0.3544
3.750 1.0276 0.01121 0.00372 -0.1358 0.4069 0.3580
4.000 1.0521 0.01135 0.00384 -0.1351 0.3963 0.3613
4.250 1.0759 0.01150 0.00399 -0.1342 0.3857 0.3652
4.500 1.1001 0.01165 0.00415 -0.1333 0.3760 0.3697
4.750 1.1241 0.01182 0.00431 -0.1325 0.3678 0.3742
5.000 1.1478 0.01200 0.00449 -0.1316 0.3594 0.3782
5.250 1.1714 0.01217 0.00468 -0.1307 0.3522 0.3824
5.500 1.1946 0.01237 0.00488 -0.1297 0.3440 0.3870
5.750 1.2175 0.01258 0.00509 -0.1287 0.3363 0.3916
6.000 1.2402 0.01279 0.00532 -0.1276 0.3282 0.3960
6.250 1.2620 0.01301 0.00556 -0.1264 0.3201 0.4008
6.500 1.2834 0.01324 0.00580 -0.1251 0.3117 0.4065
7.000 1.3248 0.01372 0.00631 -0.1223 0.2953 0.4165
7.250 1.3451 0.01398 0.00659 -0.1208 0.2872 0.4217
7.500 1.3650 0.01426 0.00688 -0.1193 0.2784 0.4268
7.750 1.3848 0.01454 0.00719 -0.1178 0.2689 0.4316
8.000 1.4032 0.01489 0.00754 -0.1161 0.2577 0.4371
8.250 1.4221 0.01523 0.00788 -0.1145 0.2469 0.4428
8.500 1.4400 0.01560 0.00826 -0.1127 0.2347 0.4484
8.750 1.4566 0.01604 0.00868 -0.1108 0.2206 0.4541
9.000 1.4721 0.01654 0.00915 -0.1087 0.2061 0.4596
9.250 1.4848 0.01718 0.00972 -0.1063 0.1880 0.4644
9.500 1.4979 0.01780 0.01030 -0.1039 0.1743 0.4701
9.750 1.5104 0.01846 0.01094 -0.1015 0.1620 0.4760
10.000 1.5226 0.01912 0.01159 -0.0991 0.1508 0.4825
10.250 1.5343 0.01981 0.01228 -0.0967 0.1417 0.4892
10.500 1.5471 0.02045 0.01295 -0.0945 0.1314 0.4960
10.750 1.5575 0.02123 0.01372 -0.0920 0.1200 0.5033
11.000 1.5651 0.02219 0.01465 -0.0894 0.1052 0.5106
11.250 1.5714 0.02324 0.01567 -0.0866 0.0925 0.5206
11.500 1.5774 0.02435 0.01678 -0.0839 0.0829 0.5326
11.750 1.5835 0.02547 0.01796 -0.0815 0.0761 0.5541
12.250 1.6307 0.02797 0.02107 -0.0845 0.0619 1.0000
12.500 1.6340 0.02957 0.02267 -0.0823 0.0562 1.0000
12.750 1.6400 0.03105 0.02420 -0.0805 0.0519 1.0000
13.000 1.6425 0.03291 0.02609 -0.0787 0.0472 1.0000
13.250 1.6454 0.03485 0.02806 -0.0772 0.0425 1.0000
13.500 1.6460 0.03710 0.03035 -0.0757 0.0381 1.0000
13.750 1.6448 0.03963 0.03291 -0.0745 0.0334 1.0000
14.000 1.6437 0.04227 0.03561 -0.0735 0.0294 1.0000
14.250 1.6406 0.04522 0.03861 -0.0726 0.0255 1.0000
14.500 1.6365 0.04838 0.04182 -0.0719 0.0226 1.0000
14.750 1.6312 0.05177 0.04528 -0.0714 0.0199 1.0000
15.000 1.6267 0.05521 0.04879 -0.0711 0.0185 1.0000
15.250 1.6214 0.05885 0.05252 -0.0710 0.0170 1.0000
15.500 1.6156 0.06264 0.05640 -0.0711 0.0161 1.0000
15.750 1.6089 0.06668 0.06053 -0.0714 0.0152 1.0000
16.000 1.6037 0.07059 0.06454 -0.0717 0.0147 1.0000
16.250 1.5970 0.07475 0.06881 -0.0722 0.0141 1.0000
16.500 1.5897 0.07905 0.07320 -0.0728 0.0136 1.0000
16.750 1.5814 0.08356 0.07782 -0.0736 0.0131 1.0000
17.000 1.5722 0.08830 0.08266 -0.0745 0.0127 1.0000
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Polar data table (+)
Polar graphs
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