GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 422 AIRFOIL (goe422-il) Reynolds number: 500,000 Max Cl/Cd: 97.36 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe422-il-500000.txt Download as CSV file: xf-goe422-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.0001 0.10300 0.10028 -0.1019 0.9070 0.0403
-10.750 0.0057 0.10045 0.09770 -0.1024 0.8938 0.0411
-10.500 -0.0191 0.09264 0.08982 -0.1089 0.8788 0.0434
-10.250 -0.0081 0.09067 0.08780 -0.1083 0.8674 0.0436
-10.000 0.0029 0.08881 0.08586 -0.1080 0.8572 0.0438
-9.750 0.0140 0.08688 0.08388 -0.1082 0.8476 0.0441
-9.500 0.0239 0.08478 0.08171 -0.1087 0.8395 0.0445
-9.250 0.0328 0.08245 0.07934 -0.1096 0.8316 0.0451
-9.000 0.0012 0.07185 0.06869 -0.1211 0.8231 0.0484
-8.750 0.0130 0.07011 0.06694 -0.1206 0.8170 0.0487
-8.500 0.0247 0.06837 0.06517 -0.1208 0.8109 0.0489
-8.250 -0.1323 0.02472 0.01939 -0.1510 0.8004 0.0385
-8.000 -0.1130 0.02306 0.01745 -0.1506 0.7951 0.0386
-7.750 -0.0922 0.02151 0.01562 -0.1502 0.7904 0.0387
-7.500 -0.0697 0.02001 0.01390 -0.1500 0.7856 0.0390
-7.250 -0.0460 0.01900 0.01282 -0.1496 0.7810 0.0394
-7.000 -0.0208 0.01835 0.01212 -0.1494 0.7761 0.0398
-6.750 0.0052 0.01780 0.01149 -0.1492 0.7716 0.0404
-6.500 0.0318 0.01723 0.01079 -0.1491 0.7671 0.0409
-6.250 0.0573 0.01658 0.01006 -0.1488 0.7626 0.0413
-6.000 0.0834 0.01598 0.00936 -0.1485 0.7576 0.0418
-5.750 0.1099 0.01545 0.00872 -0.1482 0.7530 0.0422
-5.500 0.1373 0.01501 0.00815 -0.1481 0.7485 0.0427
-5.250 0.1640 0.01463 0.00770 -0.1479 0.7438 0.0432
-5.000 0.1898 0.01400 0.00705 -0.1475 0.7386 0.0438
-4.750 0.2163 0.01358 0.00662 -0.1473 0.7334 0.0446
-4.500 0.2438 0.01330 0.00628 -0.1471 0.7277 0.0455
-4.250 0.2697 0.01298 0.00597 -0.1467 0.7208 0.0465
-4.000 0.2964 0.01272 0.00564 -0.1463 0.7137 0.0477
-3.750 0.3231 0.01241 0.00528 -0.1460 0.7075 0.0490
-3.500 0.3493 0.01212 0.00504 -0.1457 0.7013 0.0505
-3.250 0.3763 0.01191 0.00480 -0.1454 0.6954 0.0522
-3.000 0.4036 0.01174 0.00455 -0.1452 0.6896 0.0542
-2.750 0.4298 0.01149 0.00436 -0.1449 0.6830 0.0569
-2.500 0.4567 0.01132 0.00415 -0.1446 0.6764 0.0607
-2.250 0.4838 0.01120 0.00401 -0.1444 0.6703 0.0664
-2.000 0.5104 0.01104 0.00394 -0.1441 0.6634 0.0759
-1.750 0.5375 0.01099 0.00390 -0.1438 0.6565 0.0880
-1.500 0.5644 0.01095 0.00386 -0.1436 0.6496 0.0988
-1.250 0.5908 0.01087 0.00378 -0.1433 0.6418 0.1077
-1.000 0.6172 0.01085 0.00370 -0.1430 0.6344 0.1158
-0.750 0.6435 0.01076 0.00366 -0.1427 0.6263 0.1246
-0.500 0.6695 0.01071 0.00359 -0.1423 0.6187 0.1347
-0.250 0.6956 0.01065 0.00357 -0.1420 0.6110 0.1489
0.000 0.7210 0.01051 0.00357 -0.1416 0.6029 0.1952
0.250 0.7458 0.01028 0.00364 -0.1412 0.5953 0.3065
0.750 0.7907 0.00948 0.00387 -0.1395 0.5788 0.6716
1.000 0.8119 0.00936 0.00402 -0.1379 0.5694 0.7995
1.250 0.8325 0.00932 0.00410 -0.1362 0.5600 0.8605
1.500 0.8794 0.00936 0.00422 -0.1400 0.5482 1.0000
1.750 0.9021 0.00952 0.00429 -0.1390 0.5394 1.0000
2.000 0.9245 0.00969 0.00437 -0.1380 0.5301 1.0000
2.250 0.9473 0.00986 0.00447 -0.1370 0.5218 1.0000
2.500 0.9699 0.01003 0.00457 -0.1361 0.5129 1.0000
2.750 0.9921 0.01024 0.00470 -0.1350 0.5047 1.0000
3.000 1.0145 0.01042 0.00483 -0.1340 0.4957 1.0000
3.250 1.0349 0.01064 0.00497 -0.1327 0.4872 1.0000
3.500 1.0551 0.01085 0.00513 -0.1313 0.4774 1.0000
3.750 1.0745 0.01110 0.00531 -0.1298 0.4679 1.0000
4.000 1.0944 0.01136 0.00551 -0.1284 0.4578 1.0000
4.250 1.1144 0.01164 0.00573 -0.1271 0.4484 1.0000
4.500 1.1335 0.01196 0.00598 -0.1256 0.4383 1.0000
4.750 1.1538 0.01226 0.00623 -0.1244 0.4289 1.0000
5.000 1.1718 0.01264 0.00654 -0.1228 0.4191 1.0000
5.250 1.1923 0.01296 0.00682 -0.1218 0.4101 1.0000
5.500 1.2099 0.01339 0.00718 -0.1202 0.4013 1.0000
5.750 1.2304 0.01372 0.00750 -0.1192 0.3936 1.0000
6.000 1.2487 0.01415 0.00787 -0.1178 0.3860 1.0000
6.250 1.2678 0.01456 0.00825 -0.1166 0.3795 1.0000
6.500 1.2872 0.01497 0.00864 -0.1155 0.3731 1.0000
6.750 1.3045 0.01548 0.00910 -0.1141 0.3670 1.0000
7.000 1.3242 0.01589 0.00951 -0.1131 0.3618 1.0000
7.250 1.3432 0.01633 0.00995 -0.1120 0.3564 1.0000
7.500 1.3602 0.01688 0.01046 -0.1106 0.3511 1.0000
7.750 1.3781 0.01740 0.01097 -0.1094 0.3460 1.0000
8.000 1.3972 0.01787 0.01146 -0.1085 0.3412 1.0000
8.250 1.4147 0.01842 0.01200 -0.1073 0.3367 1.0000
8.500 1.4300 0.01910 0.01265 -0.1059 0.3323 1.0000
8.750 1.4486 0.01962 0.01320 -0.1049 0.3286 1.0000
9.000 1.4672 0.02016 0.01377 -0.1040 0.3246 1.0000
9.250 1.4838 0.02080 0.01443 -0.1029 0.3205 1.0000
9.500 1.4984 0.02157 0.01518 -0.1016 0.3163 1.0000
9.750 1.5146 0.02227 0.01590 -0.1005 0.3123 1.0000
10.000 1.5321 0.02291 0.01659 -0.0997 0.3077 1.0000
10.250 1.5462 0.02376 0.01744 -0.0985 0.3023 1.0000
10.500 1.5579 0.02478 0.01844 -0.0970 0.2971 1.0000
10.750 1.5749 0.02549 0.01921 -0.0962 0.2914 1.0000
11.000 1.5879 0.02647 0.02020 -0.0951 0.2855 1.0000
11.250 1.5992 0.02759 0.02132 -0.0938 0.2800 1.0000
11.500 1.6149 0.02845 0.02223 -0.0930 0.2741 1.0000
11.750 1.6240 0.02978 0.02355 -0.0916 0.2667 1.0000
12.000 1.6360 0.03093 0.02472 -0.0906 0.2577 1.0000
12.250 1.6427 0.03251 0.02628 -0.0891 0.2475 1.0000
12.500 1.6474 0.03429 0.02803 -0.0876 0.2342 1.0000
12.750 1.6473 0.03650 0.03018 -0.0858 0.2138 1.0000
13.000 1.6317 0.04009 0.03358 -0.0831 0.1828 1.0000
13.250 1.6109 0.04430 0.03764 -0.0804 0.1548 1.0000
13.500 1.5947 0.04829 0.04153 -0.0782 0.1331 1.0000
13.750 1.5825 0.05204 0.04523 -0.0765 0.1180 1.0000
14.000 1.5772 0.05526 0.04844 -0.0753 0.1106 1.0000
14.250 1.5734 0.05839 0.05159 -0.0743 0.1060 1.0000
14.500 1.5729 0.06119 0.05445 -0.0736 0.1037 1.0000
14.750 1.5715 0.06418 0.05750 -0.0729 0.1019 1.0000
15.000 1.5685 0.06740 0.06078 -0.0723 0.1003 1.0000
15.250 1.5649 0.07074 0.06418 -0.0718 0.0988 1.0000
15.500 1.5604 0.07422 0.06772 -0.0714 0.0975 1.0000
15.750 1.5546 0.07790 0.07147 -0.0710 0.0964 1.0000
16.000 1.5516 0.08130 0.07496 -0.0708 0.0958 1.0000
16.250 1.5499 0.08455 0.07830 -0.0707 0.0953 1.0000
16.500 1.5474 0.08794 0.08177 -0.0706 0.0948 1.0000
16.750 1.5443 0.09140 0.08531 -0.0706 0.0943 1.0000
17.000 1.5420 0.09474 0.08874 -0.0706 0.0937 1.0000
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