GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 449 AIRFOIL (goe449-il) Reynolds number: 500,000 Max Cl/Cd: 87.74 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe449-il-500000-n5.txt Download as CSV file: xf-goe449-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 449 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6107 0.06864 0.06516 -0.1178 0.9752 0.0272
-15.750 -0.6522 0.05669 0.05295 -0.1283 0.9703 0.0273
-15.500 -0.6717 0.04850 0.04453 -0.1364 0.9632 0.0274
-15.250 -0.6760 0.04192 0.03771 -0.1446 0.9576 0.0275
-15.000 -0.6727 0.03709 0.03268 -0.1512 0.9508 0.0277
-14.750 -0.6594 0.03363 0.02909 -0.1568 0.9446 0.0279
-14.500 -0.6385 0.03083 0.02616 -0.1623 0.9394 0.0282
-14.250 -0.6186 0.02879 0.02398 -0.1659 0.9304 0.0284
-14.000 -0.5967 0.02702 0.02207 -0.1691 0.9219 0.0286
-13.750 -0.5796 0.02571 0.02064 -0.1703 0.9112 0.0289
-13.500 -0.5654 0.02463 0.01943 -0.1703 0.9010 0.0292
-13.250 -0.5530 0.02366 0.01833 -0.1697 0.8910 0.0295
-13.000 -0.5446 0.02285 0.01740 -0.1678 0.8813 0.0296
-12.750 -0.5339 0.02213 0.01654 -0.1660 0.8727 0.0300
-12.500 -0.5258 0.02151 0.01582 -0.1634 0.8641 0.0304
-12.250 -0.5168 0.02086 0.01505 -0.1609 0.8562 0.0306
-12.000 -0.5081 0.02032 0.01440 -0.1581 0.8492 0.0309
-11.750 -0.4978 0.01986 0.01383 -0.1554 0.8425 0.0311
-11.500 -0.4834 0.01935 0.01320 -0.1535 0.8371 0.0314
-11.250 -0.4685 0.01888 0.01263 -0.1516 0.8319 0.0316
-11.000 -0.4546 0.01830 0.01200 -0.1495 0.8263 0.0319
-10.750 -0.4386 0.01780 0.01142 -0.1478 0.8207 0.0323
-10.500 -0.4216 0.01735 0.01093 -0.1461 0.8149 0.0326
-10.250 -0.4036 0.01695 0.01046 -0.1445 0.8089 0.0330
-10.000 -0.3840 0.01658 0.01002 -0.1432 0.8037 0.0334
-9.750 -0.3638 0.01622 0.00959 -0.1420 0.7992 0.0339
-9.500 -0.3437 0.01588 0.00920 -0.1407 0.7943 0.0345
-9.250 -0.3232 0.01553 0.00878 -0.1395 0.7892 0.0350
-9.000 -0.3017 0.01521 0.00837 -0.1384 0.7844 0.0355
-8.750 -0.2803 0.01491 0.00800 -0.1373 0.7795 0.0360
-8.500 -0.2598 0.01453 0.00760 -0.1360 0.7744 0.0366
-8.250 -0.2379 0.01422 0.00725 -0.1350 0.7699 0.0372
-8.000 -0.2150 0.01394 0.00692 -0.1342 0.7664 0.0379
-7.750 -0.1919 0.01368 0.00662 -0.1333 0.7630 0.0387
-7.500 -0.1689 0.01343 0.00634 -0.1324 0.7590 0.0397
-7.250 -0.1456 0.01320 0.00606 -0.1316 0.7546 0.0406
-7.000 -0.1223 0.01295 0.00577 -0.1307 0.7507 0.0418
-6.750 -0.0982 0.01273 0.00552 -0.1300 0.7471 0.0432
-6.500 -0.0744 0.01253 0.00531 -0.1293 0.7435 0.0451
-6.250 -0.0505 0.01232 0.00509 -0.1285 0.7396 0.0469
-6.000 -0.0264 0.01213 0.00489 -0.1278 0.7356 0.0491
-5.750 -0.0018 0.01197 0.00469 -0.1271 0.7316 0.0519
-5.500 0.0225 0.01180 0.00451 -0.1265 0.7276 0.0550
-5.250 0.0468 0.01165 0.00436 -0.1257 0.7232 0.0585
-5.000 0.0711 0.01150 0.00422 -0.1250 0.7187 0.0622
-4.750 0.0960 0.01140 0.00407 -0.1244 0.7146 0.0662
-4.500 0.1207 0.01127 0.00395 -0.1238 0.7106 0.0705
-4.250 0.1454 0.01117 0.00384 -0.1231 0.7061 0.0745
-4.000 0.1695 0.01103 0.00373 -0.1223 0.7012 0.0786
-3.750 0.1940 0.01095 0.00361 -0.1216 0.6962 0.0826
-3.500 0.2183 0.01085 0.00350 -0.1209 0.6911 0.0864
-3.250 0.2422 0.01075 0.00341 -0.1201 0.6852 0.0909
-3.000 0.2663 0.01069 0.00332 -0.1193 0.6796 0.0954
-2.750 0.2901 0.01058 0.00323 -0.1185 0.6743 0.1013
-2.500 0.3138 0.01051 0.00316 -0.1176 0.6678 0.1076
-2.250 0.3365 0.01042 0.00308 -0.1165 0.6610 0.1169
-2.000 0.3595 0.01034 0.00302 -0.1155 0.6538 0.1270
-1.750 0.3817 0.01028 0.00296 -0.1144 0.6458 0.1377
-1.500 0.4040 0.01020 0.00292 -0.1132 0.6384 0.1518
-1.250 0.4253 0.01014 0.00287 -0.1119 0.6295 0.1689
-1.000 0.4462 0.01007 0.00285 -0.1105 0.6207 0.1898
-0.750 0.4657 0.01002 0.00283 -0.1088 0.6108 0.2143
-0.500 0.4860 0.00997 0.00282 -0.1073 0.6018 0.2397
0.000 0.5220 0.00987 0.00282 -0.1033 0.5838 0.3002
0.250 0.5369 0.00980 0.00283 -0.1007 0.5753 0.3419
0.500 0.5536 0.00964 0.00289 -0.0986 0.5678 0.4192
0.750 0.5696 0.00958 0.00294 -0.0962 0.5605 0.4803
1.000 0.5866 0.00951 0.00301 -0.0941 0.5541 0.5305
1.250 0.5976 0.00924 0.00315 -0.0907 0.5481 0.6676
1.500 0.6117 0.00920 0.00328 -0.0878 0.5421 0.7363
1.750 0.6268 0.00911 0.00347 -0.0850 0.5370 0.8219
2.000 0.6530 0.00917 0.00371 -0.0845 0.5314 0.9025
2.250 0.6948 0.00939 0.00393 -0.0875 0.5257 0.9442
2.500 0.7443 0.00963 0.00413 -0.0923 0.5203 0.9627
2.750 0.7887 0.00984 0.00431 -0.0960 0.5140 0.9723
3.000 0.8241 0.01010 0.00449 -0.0979 0.5064 0.9804
3.250 0.8611 0.01029 0.00465 -0.1001 0.4998 0.9860
3.500 0.8955 0.01049 0.00482 -0.1018 0.4935 0.9932
4.000 0.9461 0.01086 0.00512 -0.1015 0.4846 1.0000
4.250 0.9590 0.01096 0.00522 -0.0987 0.4807 1.0000
4.500 0.9730 0.01109 0.00534 -0.0961 0.4766 1.0000
4.750 0.9867 0.01127 0.00549 -0.0935 0.4718 1.0000
5.000 1.0022 0.01146 0.00566 -0.0913 0.4675 1.0000
5.250 1.0188 0.01163 0.00583 -0.0894 0.4612 1.0000
5.500 1.0333 0.01188 0.00605 -0.0871 0.4546 1.0000
5.750 1.0494 0.01212 0.00627 -0.0851 0.4492 1.0000
6.000 1.0672 0.01233 0.00650 -0.0835 0.4432 1.0000
6.250 1.0826 0.01263 0.00677 -0.0814 0.4370 1.0000
6.500 1.0996 0.01291 0.00704 -0.0797 0.4315 1.0000
6.750 1.1172 0.01318 0.00732 -0.0782 0.4248 1.0000
7.000 1.1310 0.01358 0.00769 -0.0761 0.4175 1.0000
7.250 1.1480 0.01391 0.00802 -0.0745 0.4086 1.0000
7.500 1.1610 0.01440 0.00846 -0.0724 0.3993 1.0000
7.750 1.1769 0.01481 0.00887 -0.0707 0.3899 1.0000
8.000 1.1898 0.01536 0.00939 -0.0687 0.3794 1.0000
8.250 1.2011 0.01601 0.00998 -0.0665 0.3675 1.0000
8.500 1.2134 0.01665 0.01059 -0.0646 0.3548 1.0000
8.750 1.2260 0.01731 0.01122 -0.0628 0.3436 1.0000
9.000 1.2375 0.01806 0.01194 -0.0609 0.3335 1.0000
9.250 1.2506 0.01876 0.01261 -0.0592 0.3232 1.0000
9.500 1.2622 0.01955 0.01338 -0.0575 0.3132 1.0000
9.750 1.2728 0.02044 0.01424 -0.0557 0.3031 1.0000
10.000 1.2854 0.02125 0.01504 -0.0542 0.2935 1.0000
10.250 1.2959 0.02220 0.01596 -0.0525 0.2845 1.0000
10.500 1.3078 0.02309 0.01686 -0.0511 0.2756 1.0000
10.750 1.3181 0.02411 0.01786 -0.0495 0.2674 1.0000
11.000 1.3295 0.02510 0.01885 -0.0482 0.2591 1.0000
11.250 1.3394 0.02619 0.01993 -0.0467 0.2520 1.0000
11.500 1.3508 0.02723 0.02098 -0.0454 0.2444 1.0000
11.750 1.3582 0.02854 0.02227 -0.0439 0.2357 1.0000
12.000 1.3673 0.02979 0.02352 -0.0426 0.2268 1.0000
12.250 1.3746 0.03118 0.02490 -0.0412 0.2191 1.0000
12.500 1.3824 0.03258 0.02630 -0.0399 0.2101 1.0000
12.750 1.3901 0.03401 0.02773 -0.0386 0.2043 1.0000
13.000 1.3983 0.03543 0.02917 -0.0375 0.1958 1.0000
13.250 1.4028 0.03718 0.03090 -0.0362 0.1869 1.0000
13.500 1.4077 0.03894 0.03265 -0.0350 0.1774 1.0000
13.750 1.4127 0.04073 0.03444 -0.0339 0.1689 1.0000
14.000 1.4145 0.04281 0.03650 -0.0327 0.1590 1.0000
14.250 1.4184 0.04477 0.03847 -0.0317 0.1514 1.0000
14.500 1.4206 0.04693 0.04062 -0.0307 0.1442 1.0000
14.750 1.4234 0.04906 0.04275 -0.0299 0.1377 1.0000
15.000 1.4262 0.05123 0.04495 -0.0291 0.1332 1.0000
15.250 1.4294 0.05340 0.04715 -0.0284 0.1280 1.0000
15.500 1.4312 0.05574 0.04951 -0.0277 0.1237 1.0000
15.750 1.4333 0.05810 0.05191 -0.0271 0.1197 1.0000
16.000 1.4381 0.06020 0.05407 -0.0267 0.1166 1.0000
16.250 1.4406 0.06256 0.05646 -0.0262 0.1135 1.0000
16.500 1.4412 0.06515 0.05908 -0.0258 0.1106 1.0000
16.750 1.4444 0.06747 0.06146 -0.0255 0.1078 1.0000
17.000 1.4473 0.06986 0.06392 -0.0253 0.1043 1.0000
17.250 1.4503 0.07225 0.06636 -0.0251 0.1018 1.0000
17.500 1.4464 0.07544 0.06956 -0.0249 0.0973 1.0000
17.750 1.4514 0.07762 0.07182 -0.0248 0.0955 1.0000
18.000 1.4530 0.08022 0.07447 -0.0247 0.0915 1.0000
18.250 1.4520 0.08313 0.07741 -0.0247 0.0877 1.0000
18.500 1.4525 0.08590 0.08024 -0.0248 0.0839 1.0000
18.750 1.4505 0.08900 0.08336 -0.0250 0.0785 1.0000
19.000 1.4473 0.09222 0.08662 -0.0252 0.0737 1.0000
19.250 1.4419 0.09577 0.09018 -0.0255 0.0686 1.0000
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