GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 200,000 Max Cl/Cd: 74.23 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe190-il-200000-n5.txt Download as CSV file: xf-goe190-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3745 0.09733 0.09375 -0.0377 1.0000 0.0289
-9.750 -0.3657 0.09339 0.08982 -0.0409 0.9982 0.0296
-9.250 -0.4946 0.04742 0.04341 -0.0874 0.9762 0.0308
-9.000 -0.4611 0.03549 0.03063 -0.1125 0.9694 0.0327
-8.750 -0.4310 0.03155 0.02620 -0.1192 0.9639 0.0340
-8.500 -0.3973 0.03023 0.02479 -0.1223 0.9608 0.0349
-8.250 -0.3601 0.02876 0.02315 -0.1261 0.9583 0.0363
-8.000 -0.3369 0.02734 0.02152 -0.1267 0.9510 0.0377
-7.750 -0.3032 0.02570 0.01954 -0.1294 0.9470 0.0393
-7.500 -0.2673 0.02416 0.01775 -0.1321 0.9442 0.0405
-7.250 -0.2448 0.02325 0.01683 -0.1315 0.9359 0.0416
-7.000 -0.2114 0.02235 0.01585 -0.1331 0.9310 0.0430
-6.750 -0.1833 0.02144 0.01482 -0.1335 0.9238 0.0444
-6.500 -0.1555 0.02055 0.01380 -0.1337 0.9161 0.0456
-6.250 -0.1310 0.01984 0.01297 -0.1331 0.9064 0.0469
-5.750 -0.0804 0.01825 0.01129 -0.1323 0.8854 0.0494
-5.500 -0.0546 0.01757 0.01060 -0.1319 0.8732 0.0507
-5.250 -0.0242 0.01691 0.00990 -0.1323 0.8618 0.0521
-5.000 0.0111 0.01625 0.00916 -0.1336 0.8514 0.0543
-4.750 0.0509 0.01563 0.00844 -0.1358 0.8409 0.0566
-4.500 0.0940 0.01495 0.00768 -0.1387 0.8297 0.0588
-4.250 0.1407 0.01427 0.00691 -0.1426 0.8174 0.0619
-4.000 0.1859 0.01378 0.00625 -0.1460 0.8024 0.0659
-3.750 0.2260 0.01341 0.00568 -0.1483 0.7857 0.0706
-3.500 0.2606 0.01305 0.00516 -0.1496 0.7697 0.0773
-3.250 0.2921 0.01276 0.00474 -0.1503 0.7548 0.0881
-3.000 0.3202 0.01198 0.00431 -0.1508 0.7405 0.1991
-2.750 0.3482 0.01205 0.00441 -0.1506 0.7263 0.2565
-2.500 0.3759 0.01218 0.00440 -0.1503 0.7127 0.2748
-2.250 0.4029 0.01234 0.00446 -0.1498 0.6983 0.2876
-2.000 0.4291 0.01251 0.00454 -0.1491 0.6827 0.2985
-1.750 0.4551 0.01263 0.00450 -0.1484 0.6665 0.3078
-1.500 0.4805 0.01277 0.00461 -0.1476 0.6502 0.3148
-1.250 0.5061 0.01291 0.00463 -0.1469 0.6343 0.3234
-1.000 0.5314 0.01304 0.00470 -0.1461 0.6184 0.3299
-0.750 0.5567 0.01319 0.00477 -0.1453 0.6035 0.3364
-0.250 0.6077 0.01334 0.00469 -0.1439 0.5777 0.3448
0.000 0.6332 0.01344 0.00472 -0.1432 0.5673 0.3476
0.250 0.6587 0.01354 0.00473 -0.1426 0.5577 0.3506
0.500 0.6848 0.01363 0.00475 -0.1420 0.5492 0.3536
0.750 0.7109 0.01373 0.00476 -0.1415 0.5416 0.3568
1.000 0.7373 0.01383 0.00478 -0.1411 0.5348 0.3601
1.250 0.7634 0.01393 0.00488 -0.1406 0.5276 0.3627
1.500 0.7894 0.01409 0.00499 -0.1401 0.5212 0.3659
1.750 0.8156 0.01419 0.00510 -0.1396 0.5144 0.3695
2.000 0.8418 0.01433 0.00520 -0.1391 0.5083 0.3731
2.250 0.8682 0.01447 0.00529 -0.1387 0.5028 0.3768
2.500 0.8941 0.01457 0.00544 -0.1382 0.4963 0.3797
2.750 0.9198 0.01472 0.00559 -0.1376 0.4901 0.3829
3.000 0.9455 0.01487 0.00576 -0.1371 0.4841 0.3868
3.250 0.9711 0.01499 0.00591 -0.1365 0.4777 0.3915
3.500 0.9966 0.01516 0.00607 -0.1359 0.4720 0.3957
3.750 1.0218 0.01530 0.00628 -0.1353 0.4656 0.3995
4.000 1.0463 0.01543 0.00645 -0.1345 0.4577 0.4037
4.500 1.0946 0.01572 0.00679 -0.1329 0.4408 0.4127
4.750 1.1183 0.01588 0.00699 -0.1320 0.4327 0.4170
5.000 1.1416 0.01603 0.00719 -0.1310 0.4234 0.4223
5.250 1.1650 0.01621 0.00740 -0.1301 0.4147 0.4282
5.500 1.1876 0.01638 0.00763 -0.1290 0.4061 0.4328
5.750 1.2105 0.01657 0.00787 -0.1280 0.3980 0.4382
6.000 1.2328 0.01679 0.00811 -0.1269 0.3900 0.4440
6.250 1.2552 0.01700 0.00840 -0.1258 0.3825 0.4489
6.500 1.2771 0.01725 0.00868 -0.1246 0.3746 0.4550
6.750 1.2992 0.01751 0.00900 -0.1235 0.3666 0.4615
7.000 1.3205 0.01779 0.00933 -0.1223 0.3582 0.4677
7.250 1.3418 0.01809 0.00967 -0.1211 0.3496 0.4748
7.500 1.3613 0.01843 0.01003 -0.1196 0.3405 0.4808
7.750 1.3812 0.01874 0.01041 -0.1182 0.3306 0.4878
8.000 1.3986 0.01910 0.01080 -0.1164 0.3209 0.4948
8.250 1.4157 0.01948 0.01122 -0.1145 0.3104 0.5028
8.500 1.4332 0.01988 0.01168 -0.1127 0.3002 0.5111
8.750 1.4488 0.02035 0.01219 -0.1106 0.2906 0.5204
9.000 1.4665 0.02075 0.01270 -0.1090 0.2807 0.5304
9.250 1.4821 0.02124 0.01325 -0.1070 0.2703 0.5425
9.500 1.4961 0.02178 0.01386 -0.1049 0.2597 0.5594
9.750 1.5117 0.02225 0.01451 -0.1031 0.2477 0.5988
10.250 1.5440 0.02334 0.01602 -0.1004 0.2214 1.0000
10.500 1.5533 0.02421 0.01687 -0.0978 0.2086 1.0000
10.750 1.5605 0.02521 0.01785 -0.0951 0.1955 1.0000
11.000 1.5659 0.02636 0.01898 -0.0923 0.1832 1.0000
11.500 1.5738 0.02902 0.02162 -0.0869 0.1597 1.0000
11.750 1.5772 0.03051 0.02311 -0.0844 0.1488 1.0000
12.000 1.5788 0.03219 0.02480 -0.0821 0.1385 1.0000
12.250 1.5801 0.03401 0.02663 -0.0799 0.1278 1.0000
12.500 1.5826 0.03585 0.02852 -0.0781 0.1173 1.0000
12.750 1.5831 0.03796 0.03068 -0.0765 0.1079 1.0000
13.000 1.5815 0.04039 0.03312 -0.0750 0.0996 1.0000
13.250 1.5793 0.04300 0.03577 -0.0738 0.0916 1.0000
13.500 1.5765 0.04581 0.03862 -0.0727 0.0855 1.0000
13.750 1.5725 0.04885 0.04171 -0.0719 0.0799 1.0000
14.000 1.5684 0.05202 0.04495 -0.0713 0.0754 1.0000
14.250 1.5646 0.05528 0.04830 -0.0709 0.0706 1.0000
14.500 1.5575 0.05904 0.05213 -0.0707 0.0668 1.0000
14.750 1.5547 0.06241 0.05561 -0.0706 0.0626 1.0000
15.000 1.5484 0.06632 0.05961 -0.0709 0.0583 1.0000
15.250 1.5419 0.07038 0.06376 -0.0712 0.0547 1.0000
15.500 1.5361 0.07443 0.06791 -0.0717 0.0507 1.0000
15.750 1.5270 0.07905 0.07260 -0.0725 0.0471 1.0000
16.000 1.5208 0.08333 0.07698 -0.0733 0.0436 1.0000
16.250 1.5108 0.08827 0.08198 -0.0744 0.0402 1.0000
16.500 1.5028 0.09295 0.08677 -0.0755 0.0371 1.0000
16.750 1.4930 0.09805 0.09195 -0.0769 0.0344 1.0000
17.000 1.4838 0.10313 0.09712 -0.0784 0.0321 1.0000
17.250 1.4748 0.10826 0.10235 -0.0801 0.0299 1.0000
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Polar data table (+)
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