GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il) Reynolds number: 200,000 Max Cl/Cd: 83.64 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe239-il-200000-n5.txt Download as CSV file: xf-goe239-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 239 (MVA H.31) 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2746 0.11754 0.11387 -0.0411 1.0000 0.0253
-10.500 -0.2755 0.11465 0.11102 -0.0411 1.0000 0.0253
-10.250 -0.2788 0.11204 0.10846 -0.0405 1.0000 0.0254
-10.000 -0.2689 0.10750 0.10392 -0.0443 0.9963 0.0257
-9.750 -0.2665 0.10085 0.09727 -0.0505 0.9907 0.0270
-9.500 -0.2497 0.09798 0.09441 -0.0533 0.9862 0.0279
-9.250 -0.2350 0.09468 0.09110 -0.0563 0.9801 0.0284
-8.750 -0.2123 0.08653 0.08294 -0.0640 0.9650 0.0293
-8.500 -0.2017 0.08233 0.07873 -0.0682 0.9561 0.0305
-8.250 -0.1954 0.07665 0.07303 -0.0740 0.9460 0.0316
-7.750 -0.1831 0.06005 0.05636 -0.0943 0.9235 0.0332
-7.500 -0.1582 0.05885 0.05511 -0.0968 0.9167 0.0340
-7.250 -0.1285 0.02980 0.02488 -0.1392 0.9045 0.0364
-7.000 -0.0984 0.02582 0.02022 -0.1437 0.8984 0.0382
-6.750 -0.0688 0.02340 0.01720 -0.1460 0.8920 0.0394
-6.500 -0.0391 0.02166 0.01519 -0.1474 0.8867 0.0402
-6.250 -0.0118 0.02064 0.01403 -0.1478 0.8794 0.0410
-6.000 0.0170 0.01985 0.01310 -0.1484 0.8729 0.0421
-5.750 0.0456 0.01908 0.01215 -0.1488 0.8665 0.0436
-5.500 0.0740 0.01825 0.01111 -0.1491 0.8591 0.0448
-5.250 0.1033 0.01742 0.01007 -0.1494 0.8529 0.0458
-5.000 0.1312 0.01674 0.00923 -0.1495 0.8444 0.0468
-4.750 0.1602 0.01610 0.00843 -0.1496 0.8369 0.0478
-4.500 0.1879 0.01547 0.00778 -0.1497 0.8271 0.0494
-4.250 0.2162 0.01507 0.00732 -0.1497 0.8178 0.0514
-4.000 0.2445 0.01466 0.00683 -0.1497 0.8076 0.0533
-3.750 0.2728 0.01426 0.00635 -0.1497 0.7965 0.0552
-3.500 0.3012 0.01392 0.00590 -0.1496 0.7845 0.0571
-3.250 0.3295 0.01352 0.00547 -0.1496 0.7705 0.0600
-3.000 0.3577 0.01328 0.00516 -0.1495 0.7539 0.0640
-2.750 0.3858 0.01307 0.00484 -0.1494 0.7349 0.0692
-2.500 0.4138 0.01285 0.00454 -0.1493 0.7138 0.0762
-2.250 0.4416 0.01269 0.00425 -0.1491 0.6909 0.0849
-2.000 0.4691 0.01258 0.00399 -0.1489 0.6676 0.0976
-1.750 0.4965 0.01243 0.00377 -0.1487 0.6475 0.1197
-1.250 0.5511 0.01235 0.00378 -0.1485 0.6166 0.2268
-1.000 0.5785 0.01244 0.00381 -0.1483 0.6047 0.2514
-0.750 0.6059 0.01255 0.00386 -0.1481 0.5950 0.2695
-0.500 0.6334 0.01266 0.00392 -0.1480 0.5858 0.2863
-0.250 0.6609 0.01278 0.00399 -0.1478 0.5778 0.3014
0.000 0.6885 0.01290 0.00404 -0.1477 0.5698 0.3143
0.250 0.7160 0.01302 0.00413 -0.1476 0.5628 0.3266
0.500 0.7435 0.01313 0.00422 -0.1474 0.5556 0.3399
0.750 0.7709 0.01327 0.00431 -0.1473 0.5493 0.3533
1.000 0.7985 0.01335 0.00440 -0.1472 0.5424 0.3669
1.250 0.8257 0.01347 0.00450 -0.1470 0.5355 0.3803
1.500 0.8530 0.01359 0.00460 -0.1469 0.5293 0.3934
1.750 0.8802 0.01366 0.00471 -0.1467 0.5227 0.4074
2.000 0.9072 0.01378 0.00484 -0.1466 0.5171 0.4233
2.250 0.9346 0.01385 0.00498 -0.1465 0.5120 0.4430
2.500 0.9617 0.01388 0.00514 -0.1463 0.5065 0.4734
2.750 0.9876 0.01370 0.00535 -0.1460 0.5017 0.6240
3.000 1.0077 0.01329 0.00540 -0.1440 0.4974 1.0000
3.250 1.0349 0.01345 0.00557 -0.1438 0.4918 1.0000
3.500 1.0618 0.01365 0.00575 -0.1436 0.4860 1.0000
3.750 1.0885 0.01389 0.00593 -0.1434 0.4808 1.0000
4.000 1.1152 0.01405 0.00614 -0.1432 0.4744 1.0000
4.250 1.1416 0.01426 0.00635 -0.1429 0.4685 1.0000
4.500 1.1679 0.01449 0.00656 -0.1426 0.4630 1.0000
4.750 1.1941 0.01467 0.00680 -0.1423 0.4563 1.0000
5.000 1.2198 0.01491 0.00703 -0.1419 0.4501 1.0000
5.250 1.2456 0.01511 0.00729 -0.1416 0.4430 1.0000
5.500 1.2709 0.01534 0.00754 -0.1411 0.4356 1.0000
5.750 1.2957 0.01556 0.00781 -0.1406 0.4263 1.0000
6.000 1.3195 0.01579 0.00804 -0.1399 0.4147 1.0000
6.250 1.3425 0.01605 0.00829 -0.1390 0.4008 1.0000
6.500 1.3651 0.01635 0.00859 -0.1382 0.3868 1.0000
6.750 1.3875 0.01668 0.00892 -0.1373 0.3734 1.0000
7.000 1.4098 0.01704 0.00929 -0.1363 0.3616 1.0000
7.250 1.4312 0.01745 0.00969 -0.1353 0.3503 1.0000
7.500 1.4517 0.01790 0.01014 -0.1341 0.3389 1.0000
7.750 1.4715 0.01838 0.01061 -0.1329 0.3271 1.0000
8.000 1.4906 0.01889 0.01112 -0.1315 0.3142 1.0000
8.250 1.5092 0.01942 0.01166 -0.1301 0.3025 1.0000
8.500 1.5271 0.01999 0.01225 -0.1286 0.2933 1.0000
8.750 1.5454 0.02051 0.01284 -0.1271 0.2844 1.0000
9.000 1.5620 0.02109 0.01346 -0.1254 0.2761 1.0000
9.250 1.5750 0.02173 0.01413 -0.1230 0.2655 1.0000
9.500 1.5874 0.02244 0.01487 -0.1207 0.2524 1.0000
9.750 1.5969 0.02332 0.01574 -0.1181 0.2361 1.0000
10.000 1.6054 0.02431 0.01670 -0.1155 0.2191 1.0000
10.250 1.6124 0.02545 0.01781 -0.1129 0.2000 1.0000
10.500 1.6160 0.02688 0.01915 -0.1100 0.1700 1.0000
10.750 1.6084 0.02920 0.02121 -0.1063 0.1308 1.0000
11.000 1.6033 0.03154 0.02343 -0.1032 0.1099 1.0000
11.250 1.6016 0.03373 0.02562 -0.1007 0.0942 1.0000
11.500 1.6002 0.03601 0.02789 -0.0985 0.0784 1.0000
11.750 1.5971 0.03853 0.03041 -0.0964 0.0683 1.0000
12.000 1.5950 0.04110 0.03301 -0.0946 0.0626 1.0000
12.250 1.5923 0.04383 0.03581 -0.0931 0.0583 1.0000
12.500 1.5912 0.04651 0.03860 -0.0918 0.0548 1.0000
12.750 1.5872 0.04962 0.04181 -0.0907 0.0517 1.0000
13.000 1.5804 0.05320 0.04548 -0.0898 0.0490 1.0000
13.250 1.5798 0.05619 0.04863 -0.0893 0.0463 1.0000
13.500 1.5768 0.05959 0.05217 -0.0889 0.0433 1.0000
13.750 1.5701 0.06360 0.05628 -0.0888 0.0407 1.0000
14.000 1.5661 0.06736 0.06016 -0.0887 0.0380 1.0000
14.250 1.5621 0.07115 0.06407 -0.0888 0.0350 1.0000
14.500 1.5546 0.07552 0.06852 -0.0891 0.0327 1.0000
14.750 1.5502 0.07949 0.07261 -0.0894 0.0302 1.0000
15.000 1.5435 0.08382 0.07704 -0.0899 0.0281 1.0000
15.250 1.5352 0.08843 0.08171 -0.0905 0.0266 1.0000
15.500 1.5286 0.09284 0.08626 -0.0911 0.0251 1.0000
15.750 1.5215 0.09740 0.09092 -0.0918 0.0237 1.0000
16.000 1.5136 0.10212 0.09573 -0.0928 0.0226 1.0000
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