GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 422 AIRFOIL (goe422-il) Reynolds number: 200,000 Max Cl/Cd: 66.55 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe422-il-200000-n5.txt Download as CSV file: xf-goe422-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 422 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
------ -------- --------- --------- -------- -------- --------
-9.750 0.0063 0.08436 0.07994 -0.1137 0.8532 0.0391
-9.500 0.0117 0.08140 0.07693 -0.1147 0.8452 0.0389
-9.250 0.0152 0.07811 0.07360 -0.1161 0.8369 0.0388
-8.750 0.0156 0.07020 0.06561 -0.1205 0.8223 0.0384
-8.500 0.0103 0.06515 0.06052 -0.1240 0.8150 0.0382
-8.250 -0.1042 0.03470 0.02895 -0.1489 0.8039 0.0381
-8.000 -0.1020 0.03022 0.02383 -0.1490 0.7976 0.0384
-7.750 -0.0873 0.02759 0.02067 -0.1488 0.7926 0.0387
-7.500 -0.0688 0.02574 0.01841 -0.1484 0.7877 0.0391
-7.250 -0.0486 0.02443 0.01685 -0.1478 0.7820 0.0394
-7.000 -0.0251 0.02359 0.01591 -0.1475 0.7768 0.0397
-6.750 0.0000 0.02282 0.01502 -0.1473 0.7723 0.0402
-6.500 0.0247 0.02212 0.01420 -0.1470 0.7676 0.0406
-6.250 0.0482 0.02145 0.01344 -0.1465 0.7620 0.0411
-6.000 0.0729 0.02080 0.01266 -0.1461 0.7569 0.0417
-5.750 0.0992 0.02018 0.01187 -0.1459 0.7523 0.0426
-5.500 0.1253 0.01960 0.01112 -0.1457 0.7476 0.0436
-5.250 0.1495 0.01910 0.01058 -0.1451 0.7419 0.0444
-5.000 0.1750 0.01868 0.01015 -0.1448 0.7366 0.0452
-4.750 0.2020 0.01825 0.00965 -0.1446 0.7319 0.0460
-4.500 0.2281 0.01786 0.00919 -0.1443 0.7269 0.0470
-4.250 0.2529 0.01748 0.00878 -0.1437 0.7208 0.0481
-4.000 0.2791 0.01711 0.00834 -0.1434 0.7154 0.0493
-3.750 0.3066 0.01678 0.00798 -0.1433 0.7107 0.0506
-3.500 0.3312 0.01654 0.00774 -0.1427 0.7041 0.0524
-3.250 0.3570 0.01627 0.00743 -0.1422 0.6972 0.0548
-3.000 0.3839 0.01602 0.00714 -0.1420 0.6902 0.0576
-2.750 0.4081 0.01579 0.00691 -0.1412 0.6807 0.0610
-2.500 0.4349 0.01558 0.00665 -0.1409 0.6731 0.0652
-2.250 0.4597 0.01543 0.00653 -0.1403 0.6649 0.0705
-2.000 0.4859 0.01530 0.00639 -0.1399 0.6579 0.0780
-1.750 0.5124 0.01521 0.00628 -0.1396 0.6512 0.0872
-1.500 0.5377 0.01513 0.00620 -0.1391 0.6434 0.0964
-1.250 0.5642 0.01504 0.00605 -0.1388 0.6365 0.1054
-1.000 0.5894 0.01497 0.00599 -0.1382 0.6289 0.1145
-0.750 0.6150 0.01489 0.00589 -0.1378 0.6215 0.1254
-0.500 0.6404 0.01478 0.00582 -0.1374 0.6141 0.1400
-0.250 0.6651 0.01466 0.00580 -0.1369 0.6057 0.1636
0.000 0.6901 0.01449 0.00578 -0.1365 0.5981 0.2202
0.250 0.7140 0.01434 0.00585 -0.1359 0.5895 0.2941
0.500 0.7385 0.01420 0.00587 -0.1353 0.5818 0.3685
0.750 0.7613 0.01395 0.00598 -0.1345 0.5740 0.4862
1.000 0.7804 0.01356 0.00618 -0.1327 0.5663 0.6746
1.250 0.8005 0.01347 0.00630 -0.1307 0.5589 0.8094
1.500 0.8374 0.01341 0.00640 -0.1321 0.5498 0.9431
1.750 0.8662 0.01357 0.00643 -0.1324 0.5415 1.0000
2.000 0.8885 0.01376 0.00654 -0.1314 0.5326 1.0000
2.250 0.9105 0.01398 0.00662 -0.1304 0.5241 1.0000
2.500 0.9320 0.01419 0.00676 -0.1293 0.5148 1.0000
3.000 0.9739 0.01468 0.00706 -0.1268 0.4966 1.0000
3.250 0.9932 0.01496 0.00721 -0.1253 0.4877 1.0000
3.500 1.0122 0.01521 0.00742 -0.1238 0.4782 1.0000
3.750 1.0303 0.01553 0.00763 -0.1221 0.4692 1.0000
4.000 1.0494 0.01583 0.00789 -0.1207 0.4597 1.0000
4.500 1.0859 0.01654 0.00846 -0.1176 0.4412 1.0000
5.000 1.1219 0.01733 0.00913 -0.1147 0.4237 1.0000
5.250 1.1390 0.01778 0.00950 -0.1131 0.4158 1.0000
5.500 1.1576 0.01820 0.00989 -0.1118 0.4081 1.0000
5.750 1.1751 0.01867 0.01032 -0.1104 0.4008 1.0000
6.000 1.1926 0.01916 0.01076 -0.1090 0.3945 1.0000
6.250 1.2111 0.01963 0.01122 -0.1078 0.3881 1.0000
6.500 1.2280 0.02016 0.01171 -0.1064 0.3822 1.0000
6.750 1.2454 0.02070 0.01222 -0.1051 0.3770 1.0000
7.000 1.2634 0.02123 0.01275 -0.1040 0.3713 1.0000
7.250 1.2791 0.02185 0.01334 -0.1026 0.3653 1.0000
7.500 1.2948 0.02250 0.01396 -0.1012 0.3598 1.0000
7.750 1.3120 0.02309 0.01457 -0.1000 0.3545 1.0000
8.000 1.3283 0.02374 0.01522 -0.0988 0.3497 1.0000
8.250 1.3435 0.02446 0.01592 -0.0975 0.3453 1.0000
8.500 1.3599 0.02514 0.01660 -0.0964 0.3413 1.0000
8.750 1.3764 0.02582 0.01733 -0.0953 0.3369 1.0000
9.000 1.3917 0.02658 0.01810 -0.0941 0.3325 1.0000
9.250 1.4061 0.02739 0.01891 -0.0929 0.3284 1.0000
9.500 1.4208 0.02821 0.01973 -0.0917 0.3248 1.0000
9.750 1.4368 0.02897 0.02057 -0.0908 0.3211 1.0000
10.000 1.4513 0.02983 0.02147 -0.0897 0.3171 1.0000
10.250 1.4649 0.03075 0.02242 -0.0885 0.3131 1.0000
10.500 1.4766 0.03178 0.02344 -0.0872 0.3089 1.0000
10.750 1.4901 0.03274 0.02448 -0.0862 0.3049 1.0000
11.000 1.5036 0.03372 0.02553 -0.0852 0.3010 1.0000
11.250 1.5159 0.03480 0.02666 -0.0841 0.2972 1.0000
11.500 1.5269 0.03597 0.02786 -0.0829 0.2932 1.0000
11.750 1.5372 0.03722 0.02916 -0.0818 0.2888 1.0000
12.000 1.5474 0.03852 0.03056 -0.0808 0.2832 1.0000
12.250 1.5542 0.04010 0.03217 -0.0796 0.2770 1.0000
12.500 1.5613 0.04171 0.03383 -0.0784 0.2704 1.0000
12.750 1.5685 0.04337 0.03557 -0.0774 0.2637 1.0000
13.000 1.5728 0.04528 0.03750 -0.0762 0.2570 1.0000
13.250 1.5778 0.04721 0.03951 -0.0753 0.2477 1.0000
13.500 1.5805 0.04940 0.04174 -0.0742 0.2388 1.0000
13.750 1.5803 0.05193 0.04430 -0.0732 0.2277 1.0000
14.000 1.5771 0.05483 0.04721 -0.0722 0.2124 1.0000
14.250 1.5652 0.05872 0.05104 -0.0710 0.1916 1.0000
14.500 1.5455 0.06362 0.05586 -0.0698 0.1713 1.0000
14.750 1.5264 0.06864 0.06082 -0.0690 0.1544 1.0000
15.000 1.5088 0.07362 0.06580 -0.0684 0.1406 1.0000
15.250 1.4935 0.07849 0.07068 -0.0680 0.1294 1.0000
15.500 1.4795 0.08332 0.07554 -0.0678 0.1212 1.0000
15.750 1.4681 0.08791 0.08017 -0.0679 0.1152 1.0000
16.000 1.4571 0.09250 0.08482 -0.0680 0.1112 1.0000
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Polar data table (+)
Polar graphs
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