GOE 633 AIRFOIL (goe633-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 633 AIRFOIL (goe633-il) Reynolds number: 500,000 Max Cl/Cd: 90.83 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe633-il-500000-n5.txt Download as CSV file: xf-goe633-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7053 0.07026 0.06722 -0.0496 1.0000 0.0250
-13.250 -0.7807 0.05330 0.04997 -0.0639 1.0000 0.0248
-13.000 -0.8177 0.04199 0.03833 -0.0768 1.0000 0.0248
-12.750 -0.7963 0.03676 0.03250 -0.0870 0.8562 0.0251
-12.500 -0.8085 0.03504 0.03043 -0.0834 0.8155 0.0252
-12.250 -0.8165 0.03351 0.02866 -0.0796 0.7971 0.0252
-12.000 -0.8197 0.03216 0.02710 -0.0761 0.7841 0.0254
-11.750 -0.8148 0.03086 0.02560 -0.0735 0.7737 0.0255
-11.250 -0.7963 0.02849 0.02285 -0.0692 0.7565 0.0257
-11.000 -0.7834 0.02745 0.02162 -0.0673 0.7492 0.0258
-10.750 -0.7689 0.02643 0.02044 -0.0656 0.7428 0.0259
-10.500 -0.7547 0.02513 0.01901 -0.0639 0.7359 0.0261
-10.250 -0.7381 0.02412 0.01788 -0.0624 0.7296 0.0262
-10.000 -0.7197 0.02323 0.01692 -0.0610 0.7238 0.0264
-9.750 -0.7003 0.02245 0.01605 -0.0598 0.7180 0.0266
-9.500 -0.6802 0.02175 0.01525 -0.0586 0.7125 0.0268
-9.250 -0.6591 0.02112 0.01454 -0.0575 0.7073 0.0270
-9.000 -0.6375 0.02051 0.01386 -0.0565 0.7016 0.0273
-8.750 -0.6154 0.01996 0.01322 -0.0555 0.6961 0.0276
-8.500 -0.5931 0.01937 0.01254 -0.0545 0.6914 0.0278
-8.250 -0.5704 0.01878 0.01187 -0.0535 0.6865 0.0281
-8.000 -0.5473 0.01822 0.01123 -0.0526 0.6813 0.0283
-7.750 -0.5241 0.01770 0.01061 -0.0517 0.6762 0.0285
-7.500 -0.5003 0.01720 0.01004 -0.0509 0.6715 0.0288
-7.250 -0.4762 0.01672 0.00949 -0.0501 0.6663 0.0290
-7.000 -0.4519 0.01627 0.00897 -0.0493 0.6615 0.0292
-6.750 -0.4276 0.01586 0.00847 -0.0485 0.6572 0.0295
-6.500 -0.4025 0.01546 0.00803 -0.0478 0.6525 0.0297
-6.250 -0.3774 0.01508 0.00759 -0.0471 0.6474 0.0299
-6.000 -0.3521 0.01475 0.00719 -0.0465 0.6424 0.0301
-5.750 -0.3278 0.01428 0.00668 -0.0457 0.6381 0.0305
-5.500 -0.3026 0.01387 0.00625 -0.0450 0.6337 0.0308
-5.250 -0.2770 0.01353 0.00588 -0.0444 0.6283 0.0312
-5.000 -0.2513 0.01326 0.00555 -0.0438 0.6222 0.0317
-4.750 -0.2251 0.01298 0.00525 -0.0433 0.6159 0.0323
-4.500 -0.1988 0.01274 0.00497 -0.0428 0.6092 0.0329
-4.250 -0.1726 0.01252 0.00468 -0.0423 0.6028 0.0334
-4.000 -0.1458 0.01229 0.00442 -0.0418 0.5955 0.0339
-3.750 -0.1193 0.01210 0.00417 -0.0413 0.5884 0.0344
-3.500 -0.0924 0.01192 0.00395 -0.0409 0.5825 0.0349
-3.250 -0.0656 0.01169 0.00370 -0.0405 0.5772 0.0357
-3.000 -0.0387 0.01151 0.00349 -0.0401 0.5717 0.0367
-2.750 -0.0117 0.01135 0.00331 -0.0397 0.5662 0.0378
-2.500 0.0155 0.01121 0.00314 -0.0393 0.5602 0.0391
-2.250 0.0426 0.01109 0.00299 -0.0389 0.5547 0.0408
-2.000 0.0695 0.01094 0.00283 -0.0385 0.5498 0.0445
-1.750 0.0962 0.01072 0.00267 -0.0381 0.5443 0.0558
-1.500 0.1217 0.01039 0.00254 -0.0376 0.5382 0.1063
-1.250 0.1483 0.01027 0.00245 -0.0372 0.5325 0.1227
-1.000 0.1750 0.01014 0.00240 -0.0368 0.5256 0.1425
-0.750 0.2015 0.01006 0.00239 -0.0363 0.5194 0.1704
-0.500 0.2287 0.01002 0.00238 -0.0360 0.5136 0.1851
-0.250 0.2558 0.00999 0.00238 -0.0357 0.5069 0.1974
0.000 0.2826 0.01001 0.00236 -0.0353 0.5003 0.2065
0.250 0.3097 0.00998 0.00237 -0.0349 0.4932 0.2160
0.500 0.3365 0.01001 0.00236 -0.0345 0.4848 0.2230
0.750 0.3632 0.01000 0.00237 -0.0341 0.4764 0.2308
1.000 0.3897 0.01003 0.00238 -0.0337 0.4673 0.2405
1.250 0.4161 0.01003 0.00240 -0.0333 0.4569 0.2505
1.500 0.4422 0.01008 0.00243 -0.0328 0.4457 0.2592
1.750 0.4678 0.01014 0.00246 -0.0322 0.4320 0.2671
2.000 0.4936 0.01020 0.00251 -0.0317 0.4191 0.2763
2.250 0.5191 0.01026 0.00256 -0.0312 0.4069 0.2881
2.500 0.5441 0.01034 0.00264 -0.0306 0.3938 0.3033
2.750 0.5684 0.01042 0.00273 -0.0298 0.3799 0.3264
3.000 0.5920 0.01048 0.00283 -0.0290 0.3672 0.3618
3.250 0.6122 0.01024 0.00294 -0.0275 0.3584 0.4901
3.500 0.6515 0.00944 0.00335 -0.0297 0.3493 0.9384
3.750 0.6847 0.00967 0.00355 -0.0307 0.3418 0.9535
4.250 0.7551 0.01017 0.00395 -0.0337 0.3262 0.9658
4.500 0.7876 0.01044 0.00416 -0.0347 0.3182 0.9703
4.750 0.8259 0.01066 0.00435 -0.0369 0.3119 0.9739
5.000 0.8587 0.01087 0.00454 -0.0380 0.3068 0.9778
5.250 0.8836 0.01110 0.00474 -0.0374 0.3017 0.9814
5.500 0.9198 0.01129 0.00492 -0.0393 0.2961 0.9831
5.750 0.9536 0.01148 0.00509 -0.0406 0.2902 0.9849
6.000 0.9854 0.01173 0.00530 -0.0417 0.2842 0.9871
6.250 1.0168 0.01192 0.00550 -0.0425 0.2790 0.9894
6.500 1.0480 0.01212 0.00570 -0.0434 0.2740 0.9920
6.750 1.0842 0.01237 0.00593 -0.0454 0.2683 0.9945
7.000 1.1198 0.01256 0.00613 -0.0472 0.2632 0.9968
7.250 1.1549 0.01277 0.00634 -0.0490 0.2568 0.9989
7.500 1.1833 0.01305 0.00660 -0.0494 0.2506 1.0000
7.750 1.2035 0.01325 0.00683 -0.0481 0.2452 1.0000
8.000 1.2221 0.01352 0.00709 -0.0465 0.2380 1.0000
8.250 1.2399 0.01381 0.00737 -0.0447 0.2311 1.0000
8.500 1.2563 0.01413 0.00768 -0.0428 0.2217 1.0000
8.750 1.2716 0.01448 0.00801 -0.0407 0.2120 1.0000
9.000 1.2842 0.01491 0.00840 -0.0382 0.2001 1.0000
9.250 1.2939 0.01541 0.00884 -0.0352 0.1870 1.0000
9.500 1.3004 0.01598 0.00935 -0.0317 0.1741 1.0000
9.750 1.3019 0.01660 0.00991 -0.0273 0.1620 1.0000
10.000 1.2996 0.01710 0.01040 -0.0222 0.1543 1.0000
10.250 1.2983 0.01776 0.01103 -0.0178 0.1476 1.0000
10.500 1.3014 0.01847 0.01175 -0.0144 0.1417 1.0000
10.750 1.3048 0.01936 0.01263 -0.0114 0.1368 1.0000
11.000 1.3116 0.02026 0.01356 -0.0092 0.1328 1.0000
11.250 1.3196 0.02122 0.01455 -0.0075 0.1298 1.0000
11.500 1.3273 0.02231 0.01566 -0.0059 0.1268 1.0000
11.750 1.3340 0.02355 0.01692 -0.0044 0.1237 1.0000
12.000 1.3419 0.02478 0.01819 -0.0031 0.1208 1.0000
12.250 1.3519 0.02589 0.01936 -0.0021 0.1191 1.0000
12.500 1.3610 0.02711 0.02063 -0.0011 0.1174 1.0000
12.750 1.3688 0.02847 0.02202 -0.0001 0.1150 1.0000
13.000 1.3753 0.02996 0.02356 0.0008 0.1130 1.0000
13.250 1.3796 0.03168 0.02531 0.0017 0.1104 1.0000
13.500 1.3841 0.03342 0.02709 0.0026 0.1084 1.0000
13.750 1.3939 0.03474 0.02848 0.0032 0.1067 1.0000
14.000 1.4015 0.03626 0.03007 0.0038 0.1049 1.0000
14.250 1.4074 0.03797 0.03184 0.0044 0.1030 1.0000
14.500 1.4115 0.03986 0.03378 0.0049 0.1008 1.0000
14.750 1.4134 0.04202 0.03598 0.0054 0.0985 1.0000
15.000 1.4143 0.04437 0.03837 0.0057 0.0962 1.0000
15.250 1.4220 0.04608 0.04017 0.0059 0.0942 1.0000
15.500 1.4277 0.04804 0.04220 0.0061 0.0917 1.0000
15.750 1.4305 0.05036 0.04456 0.0062 0.0882 1.0000
16.000 1.4298 0.05310 0.04734 0.0061 0.0852 1.0000
16.250 1.4326 0.05549 0.04979 0.0061 0.0800 1.0000
16.500 1.4285 0.05876 0.05307 0.0058 0.0724 1.0000
16.750 1.4207 0.06251 0.05681 0.0053 0.0648 1.0000
17.000 1.4060 0.06719 0.06147 0.0046 0.0566 1.0000
17.250 1.3936 0.07171 0.06601 0.0037 0.0512 1.0000
17.500 1.3830 0.07609 0.07045 0.0029 0.0467 1.0000
17.750 1.3699 0.08088 0.07529 0.0018 0.0417 1.0000
18.000 1.3562 0.08588 0.08033 0.0005 0.0367 1.0000
18.250 1.3430 0.09088 0.08538 -0.0009 0.0325 1.0000
18.500 1.3281 0.09622 0.09076 -0.0024 0.0277 1.0000
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