GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 500,000 Max Cl/Cd: 100.72 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe190-il-500000.txt Download as CSV file: xf-goe190-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2464 0.10146 0.09931 -0.0425 0.9949 0.0362
-10.250 -0.2297 0.09851 0.09636 -0.0447 0.9938 0.0369
-10.000 -0.6038 0.04472 0.04191 -0.0835 0.9869 0.0266
-9.750 -0.5661 0.03852 0.03546 -0.0989 0.9836 0.0276
-9.500 -0.5291 0.03099 0.02730 -0.1147 0.9787 0.0290
-9.250 -0.4967 0.02707 0.02290 -0.1212 0.9747 0.0301
-9.000 -0.4614 0.02586 0.02166 -0.1241 0.9725 0.0310
-8.750 -0.4240 0.02500 0.02074 -0.1271 0.9709 0.0319
-8.500 -0.3857 0.02395 0.01954 -0.1303 0.9696 0.0332
-8.250 -0.3616 0.02282 0.01822 -0.1304 0.9636 0.0344
-8.000 -0.3271 0.02121 0.01635 -0.1328 0.9603 0.0356
-7.750 -0.2906 0.02001 0.01512 -0.1352 0.9581 0.0368
-7.500 -0.2513 0.01932 0.01438 -0.1379 0.9564 0.0380
-7.250 -0.2110 0.01861 0.01359 -0.1406 0.9552 0.0396
-7.000 -0.1891 0.01795 0.01283 -0.1394 0.9479 0.0407
-6.750 -0.1531 0.01740 0.01213 -0.1410 0.9448 0.0415
-6.500 -0.1180 0.01585 0.01058 -0.1429 0.9427 0.0432
-6.250 -0.0779 0.01519 0.00992 -0.1455 0.9411 0.0448
-6.000 -0.0510 0.01461 0.00930 -0.1451 0.9348 0.0461
-5.750 -0.0187 0.01398 0.00863 -0.1459 0.9297 0.0474
-5.500 0.0201 0.01347 0.00805 -0.1479 0.9268 0.0489
-5.250 0.0418 0.01270 0.00725 -0.1465 0.9169 0.0502
-5.000 0.0749 0.01193 0.00647 -0.1475 0.9099 0.0521
-4.750 0.0913 0.01148 0.00599 -0.1448 0.8903 0.0535
-4.500 0.1291 0.01095 0.00541 -0.1466 0.8746 0.0557
-4.250 0.1764 0.01050 0.00484 -0.1503 0.8556 0.0582
-4.000 0.2200 0.00984 0.00400 -0.1534 0.8270 0.0622
-3.750 0.2522 0.00967 0.00359 -0.1541 0.7985 0.0659
-3.500 0.2795 0.00962 0.00335 -0.1537 0.7759 0.0691
-3.250 0.3052 0.00942 0.00302 -0.1531 0.7563 0.0767
-3.000 0.3306 0.00923 0.00274 -0.1524 0.7390 0.0922
-2.750 0.3543 0.00855 0.00251 -0.1520 0.7242 0.2506
-2.500 0.3805 0.00868 0.00257 -0.1513 0.7102 0.2752
-2.250 0.4066 0.00883 0.00264 -0.1506 0.6959 0.2881
-2.000 0.4322 0.00895 0.00270 -0.1499 0.6808 0.2968
-1.750 0.4578 0.00910 0.00274 -0.1491 0.6645 0.3049
-1.500 0.4830 0.00917 0.00277 -0.1482 0.6465 0.3112
-1.250 0.5081 0.00929 0.00281 -0.1474 0.6269 0.3168
-1.000 0.5331 0.00944 0.00283 -0.1465 0.6073 0.3221
-0.750 0.5579 0.00955 0.00288 -0.1457 0.5905 0.3281
-0.500 0.5832 0.00971 0.00296 -0.1449 0.5774 0.3333
0.000 0.6351 0.00996 0.00305 -0.1437 0.5571 0.3425
0.250 0.6608 0.01011 0.00314 -0.1430 0.5487 0.3466
0.500 0.6876 0.01019 0.00321 -0.1426 0.5413 0.3504
0.750 0.7139 0.01031 0.00326 -0.1421 0.5346 0.3535
1.000 0.7407 0.01040 0.00331 -0.1417 0.5287 0.3561
1.250 0.7673 0.01043 0.00333 -0.1413 0.5226 0.3590
1.500 0.7935 0.01055 0.00342 -0.1408 0.5165 0.3619
1.750 0.8201 0.01061 0.00350 -0.1403 0.5107 0.3649
2.000 0.8465 0.01070 0.00359 -0.1399 0.5048 0.3684
2.250 0.8728 0.01086 0.00369 -0.1394 0.4992 0.3721
2.500 0.8992 0.01091 0.00376 -0.1390 0.4937 0.3754
2.750 0.9249 0.01096 0.00385 -0.1384 0.4870 0.3789
3.000 0.9504 0.01112 0.00397 -0.1377 0.4799 0.3824
3.250 0.9760 0.01115 0.00405 -0.1371 0.4729 0.3863
3.500 1.0014 0.01127 0.00414 -0.1365 0.4664 0.3902
3.750 1.0267 0.01133 0.00424 -0.1358 0.4596 0.3941
4.000 1.0515 0.01140 0.00435 -0.1350 0.4517 0.3982
4.250 1.0762 0.01152 0.00447 -0.1343 0.4440 0.4030
4.500 1.1010 0.01162 0.00457 -0.1335 0.4359 0.4077
4.750 1.1251 0.01173 0.00471 -0.1327 0.4287 0.4123
5.000 1.1498 0.01182 0.00486 -0.1319 0.4205 0.4171
5.250 1.1734 0.01198 0.00500 -0.1309 0.4128 0.4223
5.500 1.1976 0.01208 0.00515 -0.1301 0.4040 0.4271
5.750 1.2206 0.01225 0.00533 -0.1291 0.3956 0.4323
6.000 1.2436 0.01241 0.00550 -0.1280 0.3858 0.4380
6.250 1.2662 0.01259 0.00570 -0.1269 0.3764 0.4435
6.500 1.2876 0.01282 0.00592 -0.1256 0.3670 0.4494
6.750 1.3104 0.01301 0.00614 -0.1246 0.3577 0.4558
7.000 1.3308 0.01325 0.00639 -0.1231 0.3487 0.4614
7.250 1.3519 0.01346 0.00663 -0.1218 0.3398 0.4677
7.500 1.3715 0.01371 0.00689 -0.1202 0.3308 0.4739
7.750 1.3908 0.01395 0.00716 -0.1185 0.3217 0.4801
8.000 1.4108 0.01421 0.00745 -0.1170 0.3138 0.4873
8.250 1.4292 0.01450 0.00777 -0.1152 0.3048 0.4945
8.500 1.4489 0.01476 0.00808 -0.1137 0.2960 0.5024
8.750 1.4660 0.01511 0.00844 -0.1117 0.2858 0.5100
9.000 1.4837 0.01544 0.00879 -0.1099 0.2733 0.5186
9.250 1.5003 0.01580 0.00918 -0.1080 0.2586 0.5278
9.500 1.5160 0.01622 0.00960 -0.1059 0.2434 0.5392
9.750 1.5294 0.01674 0.01010 -0.1035 0.2260 0.5538
10.000 1.5424 0.01728 0.01068 -0.1012 0.2079 0.5832
10.250 1.5843 0.01789 0.01169 -0.1055 0.1835 1.0000
10.500 1.5960 0.01863 0.01238 -0.1031 0.1709 1.0000
10.750 1.6079 0.01937 0.01310 -0.1007 0.1603 1.0000
11.000 1.6181 0.02022 0.01392 -0.0982 0.1498 1.0000
11.250 1.6275 0.02112 0.01478 -0.0956 0.1387 1.0000
11.500 1.6378 0.02199 0.01564 -0.0933 0.1272 1.0000
11.750 1.6458 0.02301 0.01664 -0.0908 0.1149 1.0000
12.000 1.6510 0.02425 0.01782 -0.0881 0.1016 1.0000
12.250 1.6550 0.02560 0.01914 -0.0854 0.0908 1.0000
12.500 1.6582 0.02708 0.02061 -0.0828 0.0821 1.0000
12.750 1.6596 0.02877 0.02229 -0.0803 0.0749 1.0000
13.000 1.6626 0.03045 0.02400 -0.0782 0.0685 1.0000
13.250 1.6640 0.03236 0.02595 -0.0763 0.0626 1.0000
13.500 1.6632 0.03460 0.02820 -0.0745 0.0564 1.0000
13.750 1.6630 0.03692 0.03056 -0.0731 0.0499 1.0000
14.000 1.6593 0.03971 0.03338 -0.0718 0.0436 1.0000
14.250 1.6535 0.04285 0.03654 -0.0707 0.0382 1.0000
14.500 1.6458 0.04633 0.04006 -0.0698 0.0337 1.0000
14.750 1.6397 0.04977 0.04357 -0.0692 0.0305 1.0000
15.000 1.6309 0.05365 0.04751 -0.0688 0.0284 1.0000
15.250 1.6239 0.05749 0.05144 -0.0687 0.0266 1.0000
15.500 1.6162 0.06152 0.05558 -0.0688 0.0252 1.0000
15.750 1.6065 0.06592 0.06006 -0.0691 0.0241 1.0000
16.000 1.5942 0.07082 0.06505 -0.0697 0.0233 1.0000
16.250 1.5850 0.07537 0.06971 -0.0703 0.0225 1.0000
16.500 1.5770 0.07980 0.07425 -0.0710 0.0218 1.0000
16.750 1.5677 0.08448 0.07904 -0.0718 0.0212 1.0000
17.000 1.5582 0.08928 0.08395 -0.0728 0.0207 1.0000
17.250 1.5473 0.09436 0.08912 -0.0740 0.0202 1.0000
17.500 1.5356 0.09966 0.09451 -0.0754 0.0198 1.0000
17.750 1.5214 0.10550 0.10043 -0.0771 0.0193 1.0000
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