GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.32 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe190-il-1000000.txt Download as CSV file: xf-goe190-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7401 0.08525 0.08307 -0.0552 1.0000 0.0169
-14.500 -0.7750 0.07698 0.07467 -0.0593 1.0000 0.0169
-14.250 -0.7942 0.07021 0.06779 -0.0640 0.9995 0.0170
-14.000 -0.8021 0.06433 0.06180 -0.0693 0.9984 0.0171
-13.750 -0.8084 0.05889 0.05624 -0.0746 0.9969 0.0173
-13.500 -0.8092 0.05437 0.05162 -0.0794 0.9953 0.0174
-13.250 -0.8179 0.04918 0.04633 -0.0852 0.9932 0.0175
-13.000 -0.8305 0.04449 0.04157 -0.0895 0.9883 0.0179
-12.750 -0.8156 0.04006 0.03707 -0.0974 0.9855 0.0182
-12.500 -0.7896 0.03660 0.03354 -0.1050 0.9840 0.0187
-12.250 -0.7607 0.03368 0.03055 -0.1118 0.9829 0.0192
-12.000 -0.7445 0.03090 0.02768 -0.1156 0.9800 0.0195
-11.750 -0.7222 0.02841 0.02508 -0.1196 0.9772 0.0200
-11.500 -0.6904 0.02634 0.02289 -0.1243 0.9753 0.0206
-11.250 -0.6550 0.02432 0.02074 -0.1293 0.9737 0.0211
-11.000 -0.6200 0.02199 0.01832 -0.1345 0.9724 0.0220
-10.750 -0.5846 0.02079 0.01707 -0.1379 0.9716 0.0226
-10.500 -0.5492 0.01976 0.01598 -0.1409 0.9709 0.0233
-10.250 -0.5130 0.01884 0.01497 -0.1437 0.9703 0.0240
-10.000 -0.4756 0.01813 0.01416 -0.1464 0.9697 0.0247
-9.750 -0.4556 0.01778 0.01375 -0.1451 0.9658 0.0250
-9.500 -0.4290 0.01647 0.01238 -0.1461 0.9627 0.0262
-9.250 -0.3946 0.01592 0.01181 -0.1479 0.9611 0.0269
-9.000 -0.3589 0.01543 0.01127 -0.1498 0.9599 0.0277
-8.750 -0.3225 0.01491 0.01069 -0.1518 0.9590 0.0286
-8.500 -0.2843 0.01450 0.01023 -0.1540 0.9583 0.0294
-8.250 -0.2476 0.01368 0.00933 -0.1563 0.9572 0.0303
-8.000 -0.2114 0.01301 0.00865 -0.1583 0.9561 0.0314
-7.750 -0.1766 0.01260 0.00821 -0.1598 0.9544 0.0322
-7.500 -0.1582 0.01230 0.00789 -0.1577 0.9488 0.0330
-7.250 -0.1269 0.01190 0.00745 -0.1583 0.9452 0.0340
-7.000 -0.0931 0.01150 0.00700 -0.1594 0.9422 0.0347
-6.750 -0.0609 0.01111 0.00656 -0.1602 0.9391 0.0353
-6.500 -0.0422 0.01046 0.00587 -0.1585 0.9316 0.0367
-6.250 -0.0122 0.01008 0.00547 -0.1588 0.9259 0.0378
-6.000 0.0112 0.00979 0.00516 -0.1577 0.9157 0.0387
-5.750 0.0387 0.00947 0.00479 -0.1573 0.8999 0.0397
-5.500 0.0739 0.00918 0.00433 -0.1585 0.8563 0.0409
-5.250 0.0986 0.00929 0.00410 -0.1575 0.7982 0.0415
-5.000 0.1213 0.00900 0.00362 -0.1564 0.7721 0.0433
-4.750 0.1461 0.00888 0.00339 -0.1556 0.7550 0.0448
-4.500 0.1716 0.00879 0.00322 -0.1549 0.7412 0.0462
-4.250 0.1973 0.00873 0.00307 -0.1543 0.7278 0.0479
-4.000 0.2229 0.00872 0.00297 -0.1536 0.7140 0.0491
-3.750 0.2484 0.00850 0.00266 -0.1529 0.7007 0.0524
-3.500 0.2748 0.00838 0.00250 -0.1524 0.6889 0.0551
-3.250 0.3011 0.00833 0.00237 -0.1518 0.6768 0.0577
-3.000 0.3269 0.00821 0.00219 -0.1512 0.6620 0.0628
-2.750 0.3526 0.00813 0.00205 -0.1506 0.6447 0.0687
-2.500 0.3769 0.00780 0.00179 -0.1498 0.6211 0.1234
-2.250 0.3994 0.00739 0.00162 -0.1489 0.5924 0.2414
-2.000 0.4242 0.00750 0.00164 -0.1480 0.5687 0.2605
-1.750 0.4501 0.00761 0.00168 -0.1474 0.5536 0.2724
-1.500 0.4766 0.00768 0.00172 -0.1469 0.5433 0.2809
-1.250 0.5031 0.00779 0.00176 -0.1464 0.5345 0.2874
-1.000 0.5301 0.00785 0.00179 -0.1460 0.5276 0.2923
-0.750 0.5570 0.00792 0.00184 -0.1455 0.5210 0.2985
-0.500 0.5835 0.00803 0.00190 -0.1450 0.5148 0.3037
-0.250 0.6111 0.00808 0.00193 -0.1447 0.5104 0.3083
0.000 0.6380 0.00811 0.00198 -0.1443 0.5057 0.3134
0.250 0.6647 0.00820 0.00204 -0.1439 0.5007 0.3173
0.500 0.6917 0.00828 0.00210 -0.1435 0.4962 0.3212
0.750 0.7190 0.00832 0.00213 -0.1431 0.4918 0.3246
1.000 0.7457 0.00835 0.00217 -0.1427 0.4870 0.3288
1.250 0.7720 0.00843 0.00223 -0.1422 0.4821 0.3315
1.500 0.7991 0.00847 0.00228 -0.1418 0.4781 0.3342
1.750 0.8262 0.00851 0.00232 -0.1415 0.4731 0.3369
2.000 0.8524 0.00860 0.00237 -0.1409 0.4668 0.3392
2.250 0.8789 0.00865 0.00242 -0.1405 0.4612 0.3424
2.500 0.9056 0.00867 0.00248 -0.1401 0.4555 0.3462
2.750 0.9315 0.00876 0.00255 -0.1395 0.4494 0.3498
3.000 0.9580 0.00882 0.00262 -0.1390 0.4430 0.3532
3.250 0.9842 0.00890 0.00269 -0.1385 0.4355 0.3560
3.500 1.0098 0.00898 0.00277 -0.1379 0.4285 0.3599
3.750 1.0358 0.00904 0.00285 -0.1374 0.4202 0.3641
4.000 1.0611 0.00916 0.00295 -0.1367 0.4121 0.3681
4.250 1.0867 0.00925 0.00305 -0.1362 0.4036 0.3719
4.500 1.1117 0.00938 0.00316 -0.1355 0.3949 0.3759
4.750 1.1364 0.00951 0.00329 -0.1347 0.3851 0.3807
5.000 1.1611 0.00965 0.00343 -0.1340 0.3753 0.3858
5.250 1.1849 0.00984 0.00358 -0.1331 0.3641 0.3901
5.500 1.2090 0.01000 0.00374 -0.1323 0.3546 0.3952
5.750 1.2328 0.01017 0.00391 -0.1314 0.3459 0.4004
6.000 1.2561 0.01038 0.00409 -0.1304 0.3364 0.4054
6.250 1.2798 0.01055 0.00427 -0.1295 0.3277 0.4104
6.500 1.3024 0.01077 0.00448 -0.1285 0.3195 0.4158
6.750 1.3260 0.01093 0.00467 -0.1276 0.3119 0.4212
7.000 1.3473 0.01119 0.00490 -0.1262 0.3025 0.4265
7.250 1.3700 0.01133 0.00508 -0.1252 0.2956 0.4326
7.500 1.3902 0.01159 0.00532 -0.1236 0.2867 0.4381
7.750 1.4120 0.01175 0.00551 -0.1224 0.2784 0.4437
8.000 1.4320 0.01202 0.00577 -0.1209 0.2672 0.4492
8.250 1.4511 0.01234 0.00605 -0.1192 0.2535 0.4549
8.500 1.4692 0.01270 0.00636 -0.1174 0.2369 0.4602
8.750 1.4864 0.01311 0.00671 -0.1155 0.2190 0.4661
9.000 1.5014 0.01364 0.00714 -0.1132 0.1987 0.4719
9.250 1.5150 0.01421 0.00762 -0.1107 0.1801 0.4780
9.500 1.5295 0.01473 0.00810 -0.1084 0.1666 0.4844
9.750 1.5455 0.01516 0.00852 -0.1064 0.1571 0.4905
10.000 1.5609 0.01561 0.00898 -0.1043 0.1483 0.4975
10.250 1.5747 0.01615 0.00949 -0.1019 0.1383 0.5047
10.500 1.5894 0.01662 0.00998 -0.0998 0.1284 0.5142
10.750 1.6011 0.01725 0.01057 -0.0972 0.1156 0.5244
11.000 1.6102 0.01801 0.01128 -0.0944 0.1007 0.5392
11.250 1.6175 0.01882 0.01209 -0.0913 0.0878 0.5718
11.500 1.6696 0.01969 0.01351 -0.0983 0.0724 1.0000
11.750 1.6786 0.02060 0.01439 -0.0957 0.0657 1.0000
12.000 1.6899 0.02141 0.01521 -0.0935 0.0604 1.0000
12.250 1.6976 0.02244 0.01623 -0.0910 0.0542 1.0000
12.500 1.7038 0.02361 0.01738 -0.0884 0.0474 1.0000
12.750 1.7089 0.02490 0.01866 -0.0859 0.0407 1.0000
13.000 1.7122 0.02639 0.02014 -0.0834 0.0343 1.0000
13.250 1.7133 0.02812 0.02186 -0.0809 0.0285 1.0000
13.500 1.7144 0.02998 0.02374 -0.0788 0.0242 1.0000
13.750 1.7162 0.03193 0.02573 -0.0769 0.0215 1.0000
14.000 1.7165 0.03413 0.02797 -0.0753 0.0195 1.0000
14.250 1.7186 0.03628 0.03019 -0.0740 0.0183 1.0000
14.500 1.7193 0.03867 0.03265 -0.0729 0.0172 1.0000
14.750 1.7175 0.04140 0.03544 -0.0719 0.0162 1.0000
15.000 1.7142 0.04439 0.03851 -0.0710 0.0155 1.0000
15.250 1.7142 0.04710 0.04131 -0.0704 0.0151 1.0000
15.500 1.7127 0.05003 0.04433 -0.0699 0.0146 1.0000
15.750 1.7091 0.05327 0.04766 -0.0695 0.0142 1.0000
16.000 1.7039 0.05682 0.05129 -0.0693 0.0138 1.0000
16.250 1.6965 0.06076 0.05532 -0.0694 0.0134 1.0000
16.500 1.6852 0.06528 0.05995 -0.0696 0.0130 1.0000
16.750 1.6724 0.07014 0.06491 -0.0700 0.0126 1.0000
17.000 1.6666 0.07409 0.06896 -0.0704 0.0125 1.0000
17.250 1.6592 0.07826 0.07322 -0.0709 0.0123 1.0000
17.500 1.6511 0.08256 0.07762 -0.0714 0.0122 1.0000
17.750 1.6419 0.08707 0.08223 -0.0721 0.0119 1.0000
18.000 1.6322 0.09172 0.08698 -0.0730 0.0118 1.0000
18.250 1.6215 0.09656 0.09191 -0.0739 0.0116 1.0000
18.500 1.6109 0.10147 0.09692 -0.0751 0.0114 1.0000
18.750 1.6006 0.10647 0.10201 -0.0764 0.0112 1.0000
19.000 1.5896 0.11165 0.10729 -0.0779 0.0111 1.0000
19.250 1.5780 0.11700 0.11272 -0.0796 0.0109 1.0000
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