GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 628 AIRFOIL (goe628-il) Reynolds number: 500,000 Max Cl/Cd: 84.49 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe628-il-500000-n5.txt Download as CSV file: xf-goe628-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 628 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7169 0.08021 0.07687 -0.0791 1.0000 0.0355
-16.250 -0.7420 0.07334 0.06987 -0.0832 1.0000 0.0359
-16.000 -0.7626 0.06750 0.06391 -0.0865 1.0000 0.0364
-15.750 -0.7835 0.06217 0.05846 -0.0894 1.0000 0.0368
-15.500 -0.8036 0.05738 0.05356 -0.0917 1.0000 0.0371
-15.250 -0.8231 0.05299 0.04905 -0.0935 1.0000 0.0374
-15.000 -0.8396 0.04938 0.04540 -0.0944 1.0000 0.0376
-14.500 -0.8332 0.04199 0.03791 -0.1027 0.9938 0.0382
-14.250 -0.8242 0.03834 0.03419 -0.1078 0.9864 0.0386
-14.000 -0.8080 0.03469 0.03044 -0.1142 0.9803 0.0391
-13.750 -0.7938 0.03040 0.02600 -0.1223 0.9703 0.0395
-13.500 -0.7732 0.02832 0.02377 -0.1261 0.9624 0.0401
-13.250 -0.7468 0.02679 0.02210 -0.1291 0.9559 0.0408
-13.000 -0.7187 0.02549 0.02064 -0.1317 0.9495 0.0415
-12.750 -0.6920 0.02439 0.01936 -0.1335 0.9408 0.0420
-12.500 -0.6641 0.02340 0.01831 -0.1350 0.9324 0.0425
-12.250 -0.6379 0.02264 0.01750 -0.1359 0.9217 0.0430
-12.000 -0.6129 0.02207 0.01687 -0.1362 0.9104 0.0436
-11.750 -0.5882 0.02151 0.01622 -0.1363 0.8982 0.0442
-11.500 -0.5666 0.02100 0.01560 -0.1357 0.8843 0.0448
-11.250 -0.5453 0.02051 0.01500 -0.1350 0.8700 0.0455
-11.000 -0.5238 0.02007 0.01441 -0.1342 0.8546 0.0462
-10.750 -0.5020 0.01970 0.01387 -0.1334 0.8382 0.0468
-10.500 -0.4804 0.01932 0.01333 -0.1324 0.8209 0.0472
-10.250 -0.4606 0.01866 0.01258 -0.1313 0.8029 0.0476
-10.000 -0.4401 0.01813 0.01194 -0.1301 0.7858 0.0479
-9.750 -0.4188 0.01767 0.01138 -0.1291 0.7707 0.0482
-9.500 -0.3967 0.01724 0.01087 -0.1281 0.7581 0.0485
-9.250 -0.3744 0.01685 0.01039 -0.1272 0.7465 0.0488
-9.000 -0.3512 0.01648 0.00995 -0.1264 0.7361 0.0492
-8.750 -0.3277 0.01614 0.00952 -0.1256 0.7276 0.0496
-8.500 -0.3037 0.01579 0.00910 -0.1249 0.7193 0.0500
-8.250 -0.2798 0.01546 0.00869 -0.1241 0.7113 0.0504
-8.000 -0.2552 0.01513 0.00829 -0.1235 0.7045 0.0508
-7.750 -0.2305 0.01481 0.00792 -0.1228 0.6975 0.0511
-7.250 -0.1803 0.01424 0.00721 -0.1216 0.6847 0.0519
-7.000 -0.1548 0.01398 0.00689 -0.1210 0.6782 0.0523
-6.750 -0.1293 0.01376 0.00659 -0.1204 0.6719 0.0526
-6.500 -0.1034 0.01352 0.00630 -0.1199 0.6652 0.0529
-6.250 -0.0786 0.01322 0.00595 -0.1192 0.6565 0.0534
-6.000 -0.0537 0.01294 0.00561 -0.1185 0.6476 0.0539
-5.750 -0.0283 0.01269 0.00532 -0.1179 0.6377 0.0546
-5.500 -0.0027 0.01250 0.00506 -0.1173 0.6297 0.0553
-5.250 0.0238 0.01229 0.00483 -0.1169 0.6226 0.0560
-5.000 0.0499 0.01213 0.00461 -0.1164 0.6154 0.0567
-4.750 0.0765 0.01197 0.00440 -0.1159 0.6093 0.0574
-4.500 0.1033 0.01182 0.00421 -0.1155 0.6021 0.0581
-4.250 0.1295 0.01171 0.00403 -0.1149 0.5946 0.0588
-4.000 0.1563 0.01157 0.00386 -0.1145 0.5874 0.0597
-3.750 0.1827 0.01143 0.00368 -0.1140 0.5800 0.0609
-3.500 0.2091 0.01132 0.00352 -0.1136 0.5735 0.0623
-3.250 0.2360 0.01121 0.00339 -0.1131 0.5658 0.0640
-3.000 0.2622 0.01115 0.00327 -0.1126 0.5577 0.0661
-2.750 0.2888 0.01103 0.00315 -0.1121 0.5496 0.0709
-2.500 0.3141 0.01080 0.00301 -0.1116 0.5414 0.0984
-2.250 0.3398 0.01061 0.00291 -0.1111 0.5342 0.1306
-2.000 0.3657 0.01044 0.00284 -0.1106 0.5261 0.1647
-1.750 0.3914 0.01039 0.00282 -0.1100 0.5181 0.1873
-1.500 0.4178 0.01035 0.00281 -0.1095 0.5090 0.2050
-1.250 0.4434 0.01038 0.00282 -0.1089 0.4997 0.2193
-1.000 0.4697 0.01039 0.00283 -0.1084 0.4898 0.2338
-0.750 0.4952 0.01043 0.00286 -0.1078 0.4809 0.2466
-0.500 0.5213 0.01047 0.00289 -0.1072 0.4712 0.2571
-0.250 0.5468 0.01054 0.00294 -0.1066 0.4620 0.2670
0.000 0.5723 0.01061 0.00298 -0.1060 0.4515 0.2752
0.250 0.5974 0.01070 0.00304 -0.1053 0.4406 0.2856
0.750 0.6468 0.01092 0.00320 -0.1038 0.4180 0.3071
1.000 0.6711 0.01103 0.00329 -0.1029 0.4081 0.3142
1.250 0.6956 0.01115 0.00337 -0.1021 0.3978 0.3211
1.750 0.7435 0.01141 0.00359 -0.1004 0.3793 0.3375
2.000 0.7673 0.01156 0.00370 -0.0995 0.3711 0.3458
2.250 0.7907 0.01169 0.00382 -0.0986 0.3626 0.3528
2.500 0.8137 0.01185 0.00395 -0.0976 0.3551 0.3599
2.750 0.8373 0.01199 0.00407 -0.0967 0.3486 0.3668
3.000 0.8597 0.01214 0.00422 -0.0956 0.3426 0.3738
3.250 0.8825 0.01228 0.00436 -0.0946 0.3378 0.3811
3.500 0.9055 0.01241 0.00450 -0.0936 0.3329 0.3887
3.750 0.9266 0.01256 0.00466 -0.0922 0.3278 0.3974
4.250 0.9669 0.01286 0.00498 -0.0892 0.3193 0.4155
4.750 1.0077 0.01316 0.00534 -0.0863 0.3119 0.4381
5.000 1.0269 0.01335 0.00556 -0.0847 0.3084 0.4525
5.250 1.0454 0.01357 0.00582 -0.0831 0.3050 0.4699
5.500 1.0662 0.01370 0.00603 -0.0818 0.3025 0.4933
5.750 1.0859 0.01381 0.00628 -0.0803 0.2994 0.5327
6.000 1.0935 0.01334 0.00660 -0.0764 0.2966 0.8250
6.500 1.1787 0.01395 0.00731 -0.0833 0.2891 1.0000
6.750 1.1979 0.01424 0.00759 -0.0819 0.2868 1.0000
7.000 1.2185 0.01448 0.00786 -0.0808 0.2846 1.0000
7.250 1.2385 0.01476 0.00815 -0.0795 0.2821 1.0000
7.500 1.2577 0.01506 0.00846 -0.0782 0.2793 1.0000
7.750 1.2760 0.01541 0.00880 -0.0768 0.2765 1.0000
8.000 1.2937 0.01580 0.00919 -0.0753 0.2739 1.0000
8.250 1.3107 0.01623 0.00961 -0.0738 0.2715 1.0000
8.500 1.3293 0.01660 0.01000 -0.0726 0.2694 1.0000
8.750 1.3488 0.01695 0.01039 -0.0715 0.2670 1.0000
9.000 1.3671 0.01735 0.01082 -0.0703 0.2642 1.0000
9.250 1.3846 0.01780 0.01128 -0.0691 0.2612 1.0000
9.500 1.4000 0.01835 0.01182 -0.0676 0.2573 1.0000
9.750 1.4146 0.01897 0.01243 -0.0661 0.2537 1.0000
10.000 1.4330 0.01942 0.01294 -0.0651 0.2514 1.0000
10.250 1.4505 0.01994 0.01349 -0.0641 0.2490 1.0000
10.500 1.4671 0.02051 0.01411 -0.0630 0.2464 1.0000
10.750 1.4823 0.02118 0.01479 -0.0618 0.2435 1.0000
11.000 1.4963 0.02193 0.01555 -0.0605 0.2407 1.0000
11.250 1.5094 0.02276 0.01640 -0.0593 0.2382 1.0000
11.500 1.5260 0.02341 0.01711 -0.0584 0.2363 1.0000
11.750 1.5419 0.02412 0.01788 -0.0575 0.2339 1.0000
12.000 1.5565 0.02492 0.01873 -0.0565 0.2312 1.0000
12.250 1.5699 0.02583 0.01967 -0.0556 0.2284 1.0000
12.500 1.5809 0.02692 0.02078 -0.0545 0.2252 1.0000
12.750 1.5916 0.02807 0.02196 -0.0534 0.2223 1.0000
13.000 1.6061 0.02897 0.02293 -0.0527 0.2200 1.0000
13.250 1.6189 0.03002 0.02405 -0.0519 0.2172 1.0000
13.500 1.6297 0.03123 0.02530 -0.0511 0.2136 1.0000
13.750 1.6370 0.03276 0.02684 -0.0502 0.2096 1.0000
14.000 1.6461 0.03418 0.02831 -0.0494 0.2053 1.0000
14.250 1.6552 0.03563 0.02981 -0.0488 0.2002 1.0000
14.500 1.6596 0.03751 0.03171 -0.0479 0.1954 1.0000
14.750 1.6658 0.03927 0.03351 -0.0473 0.1914 1.0000
15.000 1.6725 0.04100 0.03529 -0.0467 0.1863 1.0000
15.250 1.6710 0.04356 0.03786 -0.0459 0.1800 1.0000
15.500 1.6760 0.04553 0.03988 -0.0454 0.1754 1.0000
15.750 1.6754 0.04808 0.04246 -0.0449 0.1693 1.0000
16.000 1.6743 0.05073 0.04514 -0.0444 0.1642 1.0000
16.250 1.6742 0.05334 0.04780 -0.0441 0.1588 1.0000
16.500 1.6666 0.05679 0.05127 -0.0438 0.1530 1.0000
16.750 1.6631 0.05986 0.05439 -0.0436 0.1469 1.0000
17.000 1.6573 0.06326 0.05783 -0.0435 0.1426 1.0000
17.250 1.6490 0.06699 0.06161 -0.0435 0.1370 1.0000
17.500 1.6399 0.07087 0.06553 -0.0436 0.1318 1.0000
17.750 1.6295 0.07499 0.06970 -0.0439 0.1281 1.0000
18.000 1.6218 0.07885 0.07363 -0.0442 0.1240 1.0000
18.250 1.6109 0.08315 0.07798 -0.0447 0.1203 1.0000
18.500 1.5966 0.08796 0.08285 -0.0454 0.1169 1.0000
18.750 1.5904 0.09177 0.08674 -0.0460 0.1140 1.0000
19.000 1.5795 0.09628 0.09131 -0.0469 0.1105 1.0000
19.250 1.5643 0.10141 0.09650 -0.0480 0.1072 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 628 AIRFOIL (goe628-il)