GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 100,000 Max Cl/Cd: 43.87 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe633-il-100000.txt Download as CSV file: xf-goe633-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 633 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2681 0.09882 0.09430 -0.0315 1.0000 0.1476
-8.750 -0.3106 0.09876 0.09450 -0.0346 1.0000 0.1512
-8.500 -0.3077 0.09488 0.09069 -0.0375 0.9853 0.1528
-8.250 -0.2632 0.09067 0.08643 -0.0377 0.9777 0.1562
-8.000 -0.2373 0.08653 0.08226 -0.0437 0.9657 0.1618
-7.750 -0.2477 0.08090 0.07660 -0.0585 0.9441 0.1681
-7.500 -0.2061 0.07677 0.07243 -0.0593 0.9376 0.1705
-7.250 -0.3232 0.04840 0.04294 -0.0790 0.9097 0.0965
-7.000 -0.3077 0.04484 0.03920 -0.0794 0.9001 0.0950
-6.750 -0.3043 0.04088 0.03489 -0.0781 0.8885 0.0932
-6.500 -0.3005 0.03695 0.03044 -0.0763 0.8788 0.0917
-6.250 -0.2901 0.03426 0.02726 -0.0744 0.8694 0.0921
-6.000 -0.2762 0.03226 0.02485 -0.0725 0.8605 0.0931
-5.750 -0.2592 0.03051 0.02267 -0.0708 0.8519 0.0943
-5.500 -0.2398 0.02901 0.02077 -0.0692 0.8445 0.0954
-5.250 -0.2194 0.02781 0.01921 -0.0678 0.8360 0.0966
-5.000 -0.1941 0.02654 0.01779 -0.0670 0.8299 0.0987
-4.750 -0.1728 0.02587 0.01713 -0.0660 0.8209 0.1014
-4.500 -0.1476 0.02516 0.01628 -0.0651 0.8143 0.1059
-4.250 -0.1249 0.02455 0.01558 -0.0641 0.8065 0.1115
-4.000 -0.1010 0.02405 0.01509 -0.0631 0.7990 0.1194
-3.750 -0.0767 0.02347 0.01455 -0.0621 0.7927 0.1304
-3.500 -0.0555 0.02311 0.01432 -0.0608 0.7840 0.1531
-3.250 -0.0337 0.02342 0.01468 -0.0587 0.7775 0.1973
-3.000 -0.0160 0.02386 0.01515 -0.0569 0.7670 0.2229
-2.750 0.0083 0.02392 0.01512 -0.0554 0.7600 0.2434
-2.500 0.0278 0.02414 0.01534 -0.0540 0.7497 0.2604
-2.250 0.0526 0.02408 0.01522 -0.0527 0.7430 0.2790
-2.000 0.0732 0.02419 0.01535 -0.0515 0.7338 0.2954
-1.750 0.0977 0.02405 0.01520 -0.0505 0.7269 0.3149
-1.500 0.1205 0.02400 0.01516 -0.0494 0.7192 0.3327
-1.250 0.1453 0.02380 0.01494 -0.0486 0.7110 0.3482
-1.000 0.1748 0.02342 0.01445 -0.0481 0.7057 0.3632
-0.750 0.1966 0.02341 0.01457 -0.0473 0.6951 0.3762
-0.500 0.2262 0.02297 0.01413 -0.0469 0.6891 0.3933
-0.250 0.2502 0.02298 0.01425 -0.0463 0.6793 0.4107
0.000 0.2824 0.02257 0.01389 -0.0465 0.6724 0.4349
0.250 0.3115 0.02237 0.01390 -0.0466 0.6634 0.4669
0.500 0.3402 0.02164 0.01359 -0.0462 0.6554 0.5433
0.750 0.5330 0.02040 0.01299 -0.0761 0.6419 1.0000
1.000 0.5581 0.02029 0.01267 -0.0748 0.6349 1.0000
1.250 0.5793 0.02057 0.01289 -0.0736 0.6238 1.0000
1.500 0.6048 0.02041 0.01255 -0.0724 0.6168 1.0000
1.750 0.6255 0.02071 0.01282 -0.0711 0.6053 1.0000
2.000 0.6517 0.02055 0.01248 -0.0700 0.5988 1.0000
2.250 0.6718 0.02090 0.01283 -0.0687 0.5869 1.0000
2.500 0.6988 0.02070 0.01244 -0.0677 0.5806 1.0000
2.750 0.7183 0.02106 0.01283 -0.0663 0.5683 1.0000
3.000 0.7423 0.02112 0.01279 -0.0651 0.5600 1.0000
3.250 0.7646 0.02132 0.01294 -0.0639 0.5502 1.0000
3.500 0.7874 0.02156 0.01312 -0.0628 0.5418 1.0000
3.750 0.8099 0.02178 0.01330 -0.0616 0.5329 1.0000
4.000 0.8326 0.02203 0.01351 -0.0605 0.5248 1.0000
4.250 0.8545 0.02231 0.01376 -0.0593 0.5160 1.0000
4.500 0.8786 0.02252 0.01389 -0.0583 0.5093 1.0000
4.750 0.8974 0.02306 0.01448 -0.0569 0.5004 1.0000
5.000 0.9256 0.02297 0.01423 -0.0563 0.4947 1.0000
5.250 0.9403 0.02369 0.01508 -0.0544 0.4848 1.0000
5.500 0.9684 0.02351 0.01475 -0.0538 0.4782 1.0000
5.750 0.9833 0.02417 0.01553 -0.0518 0.4688 1.0000
6.000 1.0110 0.02398 0.01517 -0.0511 0.4617 1.0000
6.250 1.0259 0.02455 0.01586 -0.0491 0.4522 1.0000
6.500 1.0534 0.02438 0.01554 -0.0485 0.4449 1.0000
6.750 1.0675 0.02501 0.01630 -0.0464 0.4361 1.0000
7.000 1.0918 0.02514 0.01638 -0.0455 0.4295 1.0000
7.250 1.1093 0.02574 0.01704 -0.0439 0.4228 1.0000
7.500 1.1275 0.02621 0.01756 -0.0423 0.4156 1.0000
7.750 1.1548 0.02634 0.01757 -0.0418 0.4097 1.0000
8.000 1.1643 0.02718 0.01861 -0.0392 0.4017 1.0000
8.250 1.1923 0.02718 0.01849 -0.0388 0.3950 1.0000
8.500 1.2016 0.02802 0.01950 -0.0361 0.3869 1.0000
8.750 1.2266 0.02812 0.01953 -0.0353 0.3793 1.0000
9.000 1.2376 0.02887 0.02041 -0.0329 0.3711 1.0000
9.250 1.2614 0.02903 0.02049 -0.0320 0.3629 1.0000
9.500 1.2708 0.02984 0.02142 -0.0294 0.3543 1.0000
9.750 1.2965 0.03000 0.02148 -0.0287 0.3455 1.0000
10.000 1.3002 0.03096 0.02261 -0.0254 0.3362 1.0000
10.250 1.3290 0.03114 0.02262 -0.0252 0.3266 1.0000
10.500 1.3274 0.03217 0.02386 -0.0212 0.3168 1.0000
10.750 1.3438 0.03282 0.02447 -0.0196 0.3069 1.0000
11.000 1.3567 0.03344 0.02508 -0.0174 0.2969 1.0000
11.250 1.3572 0.03460 0.02634 -0.0140 0.2879 1.0000
11.500 1.3847 0.03493 0.02649 -0.0137 0.2785 1.0000
11.750 1.3699 0.03653 0.02833 -0.0086 0.2716 1.0000
12.000 1.3873 0.03719 0.02895 -0.0073 0.2643 1.0000
12.250 1.3873 0.03855 0.03040 -0.0041 0.2587 1.0000
12.500 1.3750 0.04024 0.03226 0.0001 0.2537 1.0000
12.750 1.4049 0.04066 0.03259 0.0000 0.2478 1.0000
13.000 1.3978 0.04255 0.03461 0.0030 0.2436 1.0000
13.250 1.3757 0.04520 0.03749 0.0064 0.2398 1.0000
13.500 1.3762 0.04694 0.03933 0.0081 0.2356 1.0000
13.750 1.4223 0.04652 0.03876 0.0075 0.2304 1.0000
14.000 1.3811 0.05072 0.04327 0.0106 0.2280 1.0000
14.250 1.3324 0.05655 0.04938 0.0123 0.2256 1.0000
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Polar data table (+)
Polar graphs
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