GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 620 AIRFOIL (goe620-il) Reynolds number: 500,000 Max Cl/Cd: 82.52 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe620-il-500000-n5.txt Download as CSV file: xf-goe620-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 620 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.5662 0.07983 0.07631 -0.1085 0.9835 0.0325
-16.000 -0.5824 0.07250 0.06886 -0.1149 0.9810 0.0327
-15.750 -0.5966 0.06665 0.06291 -0.1193 0.9751 0.0328
-15.500 -0.6058 0.06111 0.05727 -0.1243 0.9705 0.0330
-15.250 -0.6095 0.05617 0.05224 -0.1293 0.9661 0.0331
-15.000 -0.6143 0.05139 0.04735 -0.1340 0.9592 0.0333
-14.750 -0.6109 0.04670 0.04254 -0.1400 0.9542 0.0335
-14.500 -0.6038 0.04270 0.03844 -0.1453 0.9468 0.0337
-14.250 -0.5897 0.03854 0.03415 -0.1523 0.9403 0.0339
-14.000 -0.5676 0.03485 0.03032 -0.1599 0.9335 0.0342
-13.750 -0.5436 0.03157 0.02688 -0.1671 0.9238 0.0346
-13.500 -0.5224 0.02875 0.02389 -0.1729 0.9112 0.0349
-13.250 -0.5060 0.02646 0.02142 -0.1770 0.8966 0.0352
-13.000 -0.4978 0.02478 0.01956 -0.1781 0.8813 0.0355
-12.750 -0.4920 0.02367 0.01828 -0.1771 0.8671 0.0358
-12.500 -0.4890 0.02280 0.01727 -0.1746 0.8537 0.0361
-12.250 -0.4850 0.02211 0.01644 -0.1717 0.8424 0.0363
-12.000 -0.4777 0.02152 0.01570 -0.1692 0.8318 0.0366
-11.750 -0.4675 0.02087 0.01496 -0.1670 0.8224 0.0369
-11.500 -0.4550 0.02027 0.01427 -0.1651 0.8139 0.0371
-11.250 -0.4406 0.01972 0.01366 -0.1634 0.8069 0.0375
-11.000 -0.4244 0.01923 0.01310 -0.1618 0.8000 0.0378
-10.750 -0.4067 0.01878 0.01257 -0.1605 0.7938 0.0381
-10.500 -0.3884 0.01835 0.01208 -0.1592 0.7878 0.0385
-10.250 -0.3694 0.01793 0.01159 -0.1579 0.7819 0.0389
-10.000 -0.3494 0.01753 0.01110 -0.1568 0.7768 0.0393
-9.750 -0.3289 0.01714 0.01065 -0.1557 0.7721 0.0399
-9.500 -0.3082 0.01675 0.01019 -0.1546 0.7669 0.0403
-9.250 -0.2868 0.01641 0.00975 -0.1536 0.7615 0.0408
-9.000 -0.2645 0.01611 0.00935 -0.1527 0.7565 0.0413
-8.750 -0.2436 0.01569 0.00891 -0.1516 0.7516 0.0419
-8.500 -0.2219 0.01533 0.00851 -0.1506 0.7468 0.0424
-8.250 -0.1992 0.01503 0.00816 -0.1497 0.7424 0.0430
-7.750 -0.1524 0.01446 0.00750 -0.1482 0.7349 0.0442
-7.500 -0.1288 0.01418 0.00719 -0.1474 0.7309 0.0449
-7.250 -0.1049 0.01393 0.00689 -0.1466 0.7269 0.0456
-7.000 -0.0805 0.01371 0.00660 -0.1459 0.7231 0.0463
-6.750 -0.0562 0.01347 0.00629 -0.1453 0.7196 0.0470
-6.500 -0.0326 0.01317 0.00599 -0.1445 0.7161 0.0479
-6.250 -0.0083 0.01292 0.00574 -0.1438 0.7123 0.0489
-6.000 0.0164 0.01272 0.00551 -0.1431 0.7084 0.0499
-5.750 0.0414 0.01254 0.00528 -0.1425 0.7047 0.0510
-5.500 0.0668 0.01239 0.00506 -0.1419 0.7011 0.0520
-5.250 0.0917 0.01219 0.00485 -0.1413 0.6977 0.0530
-5.000 0.1163 0.01196 0.00462 -0.1406 0.6937 0.0543
-4.750 0.1412 0.01178 0.00443 -0.1400 0.6895 0.0558
-4.500 0.1666 0.01165 0.00425 -0.1394 0.6856 0.0575
-4.250 0.1922 0.01153 0.00408 -0.1388 0.6819 0.0593
-4.000 0.2170 0.01134 0.00392 -0.1382 0.6778 0.0617
-3.750 0.2421 0.01120 0.00378 -0.1375 0.6734 0.0647
-3.500 0.2670 0.01106 0.00364 -0.1368 0.6690 0.0693
-3.250 0.2916 0.01090 0.00351 -0.1361 0.6646 0.0804
-3.000 0.3161 0.01072 0.00341 -0.1354 0.6601 0.0994
-2.750 0.3407 0.01058 0.00332 -0.1347 0.6550 0.1141
-2.500 0.3650 0.01046 0.00323 -0.1339 0.6500 0.1292
-2.250 0.3893 0.01036 0.00316 -0.1331 0.6450 0.1466
-2.000 0.4137 0.01025 0.00313 -0.1323 0.6393 0.1663
-1.750 0.4377 0.01018 0.00309 -0.1315 0.6332 0.1827
-1.500 0.4614 0.01014 0.00305 -0.1305 0.6275 0.1976
-1.250 0.4856 0.01008 0.00304 -0.1297 0.6210 0.2110
-1.000 0.5088 0.01006 0.00302 -0.1286 0.6137 0.2224
-0.750 0.5316 0.01004 0.00301 -0.1275 0.6063 0.2350
-0.500 0.5526 0.01004 0.00300 -0.1260 0.5958 0.2459
-0.250 0.5734 0.01006 0.00300 -0.1245 0.5851 0.2585
0.000 0.5913 0.01010 0.00301 -0.1224 0.5725 0.2720
0.250 0.6085 0.01014 0.00303 -0.1201 0.5608 0.2843
0.500 0.6255 0.01020 0.00306 -0.1178 0.5489 0.2989
0.750 0.6419 0.01027 0.00312 -0.1154 0.5386 0.3151
1.000 0.6601 0.01034 0.00320 -0.1134 0.5280 0.3314
1.250 0.6774 0.01045 0.00331 -0.1113 0.5183 0.3505
1.500 0.6960 0.01055 0.00343 -0.1094 0.5091 0.3700
1.750 0.7147 0.01066 0.00355 -0.1076 0.5019 0.3892
2.000 0.7342 0.01075 0.00368 -0.1059 0.4941 0.4103
2.250 0.7509 0.01092 0.00384 -0.1038 0.4852 0.4272
2.500 0.7705 0.01103 0.00398 -0.1022 0.4770 0.4465
2.750 0.7874 0.01119 0.00416 -0.1001 0.4693 0.4682
3.000 0.8068 0.01129 0.00433 -0.0985 0.4626 0.4955
3.250 0.8241 0.01142 0.00452 -0.0965 0.4545 0.5297
3.500 0.8408 0.01157 0.00473 -0.0944 0.4474 0.5638
3.750 0.8587 0.01169 0.00493 -0.0926 0.4400 0.5987
4.250 0.8874 0.01184 0.00541 -0.0875 0.4256 0.7209
4.750 1.0150 0.01230 0.00622 -0.1038 0.4004 1.0000
5.000 1.0322 0.01263 0.00650 -0.1021 0.3925 1.0000
5.250 1.0496 0.01297 0.00679 -0.1004 0.3838 1.0000
5.500 1.0663 0.01334 0.00713 -0.0986 0.3756 1.0000
5.750 1.0828 0.01375 0.00748 -0.0969 0.3660 1.0000
6.000 1.0995 0.01417 0.00786 -0.0952 0.3576 1.0000
6.250 1.1156 0.01463 0.00828 -0.0935 0.3485 1.0000
6.500 1.1313 0.01513 0.00873 -0.0919 0.3383 1.0000
6.750 1.1448 0.01574 0.00928 -0.0899 0.3271 1.0000
7.000 1.1600 0.01631 0.00981 -0.0883 0.3165 1.0000
7.250 1.1743 0.01695 0.01040 -0.0866 0.3068 1.0000
7.500 1.1888 0.01760 0.01100 -0.0850 0.2977 1.0000
7.750 1.2039 0.01824 0.01162 -0.0835 0.2899 1.0000
8.000 1.2181 0.01895 0.01229 -0.0819 0.2816 1.0000
8.250 1.2327 0.01966 0.01298 -0.0805 0.2746 1.0000
8.500 1.2472 0.02039 0.01369 -0.0791 0.2672 1.0000
8.750 1.2600 0.02124 0.01452 -0.0776 0.2604 1.0000
9.000 1.2756 0.02194 0.01522 -0.0764 0.2550 1.0000
9.250 1.2888 0.02281 0.01608 -0.0751 0.2487 1.0000
9.500 1.3023 0.02368 0.01694 -0.0738 0.2439 1.0000
9.750 1.3176 0.02446 0.01773 -0.0727 0.2397 1.0000
10.000 1.3318 0.02531 0.01859 -0.0716 0.2354 1.0000
10.250 1.3433 0.02636 0.01964 -0.0702 0.2300 1.0000
10.500 1.3568 0.02731 0.02059 -0.0691 0.2256 1.0000
10.750 1.3714 0.02819 0.02150 -0.0681 0.2217 1.0000
11.000 1.3830 0.02929 0.02261 -0.0670 0.2166 1.0000
11.250 1.3935 0.03049 0.02380 -0.0657 0.2123 1.0000
11.500 1.4075 0.03145 0.02481 -0.0648 0.2087 1.0000
11.750 1.4199 0.03255 0.02593 -0.0639 0.2035 1.0000
12.000 1.4295 0.03388 0.02726 -0.0627 0.1984 1.0000
12.250 1.4400 0.03516 0.02856 -0.0617 0.1922 1.0000
12.500 1.4469 0.03673 0.03011 -0.0605 0.1825 1.0000
12.750 1.4517 0.03852 0.03186 -0.0592 0.1690 1.0000
13.000 1.4474 0.04112 0.03434 -0.0575 0.1474 1.0000
13.250 1.4464 0.04349 0.03666 -0.0560 0.1369 1.0000
13.500 1.4487 0.04562 0.03878 -0.0549 0.1312 1.0000
13.750 1.4533 0.04761 0.04080 -0.0539 0.1279 1.0000
14.000 1.4562 0.04977 0.04298 -0.0530 0.1242 1.0000
14.250 1.4594 0.05197 0.04521 -0.0522 0.1219 1.0000
14.500 1.4628 0.05417 0.04744 -0.0514 0.1195 1.0000
14.750 1.4675 0.05628 0.04960 -0.0507 0.1175 1.0000
15.000 1.4733 0.05830 0.05169 -0.0502 0.1162 1.0000
15.250 1.4778 0.06048 0.05393 -0.0496 0.1148 1.0000
15.500 1.4813 0.06279 0.05629 -0.0491 0.1131 1.0000
15.750 1.4850 0.06510 0.05866 -0.0487 0.1121 1.0000
16.000 1.4868 0.06764 0.06125 -0.0483 0.1108 1.0000
16.250 1.4886 0.07019 0.06386 -0.0479 0.1096 1.0000
16.500 1.4877 0.07312 0.06684 -0.0476 0.1080 1.0000
16.750 1.4870 0.07601 0.06978 -0.0474 0.1065 1.0000
17.000 1.4929 0.07819 0.07204 -0.0473 0.1055 1.0000
17.250 1.4981 0.08041 0.07434 -0.0471 0.1044 1.0000
17.500 1.5013 0.08291 0.07691 -0.0471 0.1034 1.0000
17.750 1.5050 0.08534 0.07942 -0.0471 0.1021 1.0000
18.000 1.5060 0.08814 0.08229 -0.0471 0.1005 1.0000
18.250 1.5076 0.09086 0.08506 -0.0472 0.0994 1.0000
18.500 1.5065 0.09393 0.08820 -0.0474 0.0980 1.0000
18.750 1.5056 0.09699 0.09130 -0.0476 0.0967 1.0000
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