GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 500,000 Max Cl/Cd: 91.14 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe655-il-500000.txt Download as CSV file: xf-goe655-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3105 0.11957 0.11717 -0.0379 1.0000 0.0328
-11.750 -0.3090 0.11655 0.11417 -0.0384 1.0000 0.0336
-11.500 -0.7114 0.04496 0.04206 -0.0763 1.0000 0.0265
-11.250 -0.3406 0.10342 0.10112 -0.0440 1.0000 0.0364
-11.000 -0.3338 0.10232 0.10003 -0.0426 1.0000 0.0367
-10.750 -0.4437 0.07665 0.07442 -0.0522 1.0000 0.0311
-10.500 -0.6188 0.03986 0.03686 -0.0849 0.9871 0.0286
-10.250 -0.6123 0.03379 0.03021 -0.0896 0.9817 0.0294
-10.000 -0.6010 0.03004 0.02596 -0.0906 0.9743 0.0301
-9.750 -0.5769 0.02709 0.02254 -0.0927 0.9710 0.0311
-9.500 -0.5430 0.02571 0.02114 -0.0951 0.9695 0.0319
-9.250 -0.5187 0.02503 0.02043 -0.0949 0.9628 0.0326
-9.000 -0.4864 0.02382 0.01910 -0.0966 0.9598 0.0334
-8.750 -0.4524 0.02237 0.01743 -0.0986 0.9576 0.0344
-8.500 -0.4171 0.02125 0.01606 -0.1005 0.9556 0.0355
-8.250 -0.3947 0.02019 0.01478 -0.0998 0.9478 0.0362
-8.000 -0.3642 0.01859 0.01313 -0.1009 0.9434 0.0372
-7.750 -0.3308 0.01778 0.01227 -0.1021 0.9390 0.0380
-7.500 -0.3062 0.01715 0.01157 -0.1014 0.9290 0.0389
-7.250 -0.2765 0.01652 0.01085 -0.1017 0.9208 0.0400
-7.000 -0.2498 0.01591 0.01011 -0.1013 0.9098 0.0410
-6.750 -0.2244 0.01539 0.00947 -0.1006 0.8971 0.0416
-6.500 -0.1993 0.01452 0.00848 -0.0999 0.8839 0.0425
-6.250 -0.1745 0.01374 0.00766 -0.0993 0.8709 0.0435
-6.000 -0.1486 0.01335 0.00723 -0.0987 0.8579 0.0448
-5.750 -0.1237 0.01298 0.00679 -0.0979 0.8434 0.0460
-5.500 -0.0987 0.01261 0.00633 -0.0972 0.8290 0.0471
-5.250 -0.0735 0.01230 0.00592 -0.0964 0.8149 0.0482
-5.000 -0.0485 0.01197 0.00549 -0.0956 0.8013 0.0493
-4.750 -0.0251 0.01146 0.00493 -0.0947 0.7883 0.0513
-4.500 0.0001 0.01123 0.00463 -0.0939 0.7755 0.0532
-4.250 0.0252 0.01103 0.00436 -0.0932 0.7626 0.0553
-4.000 0.0508 0.01087 0.00411 -0.0925 0.7507 0.0570
-3.750 0.0748 0.01051 0.00371 -0.0916 0.7392 0.0608
-3.500 0.1002 0.01036 0.00349 -0.0909 0.7280 0.0647
-3.250 0.1254 0.01012 0.00323 -0.0902 0.7173 0.0711
-3.000 0.1506 0.00993 0.00301 -0.0895 0.7070 0.0816
-2.750 0.1749 0.00960 0.00281 -0.0887 0.6960 0.1145
-2.500 0.1989 0.00925 0.00270 -0.0879 0.6854 0.1822
-2.250 0.2237 0.00910 0.00262 -0.0872 0.6742 0.2266
-2.000 0.2488 0.00897 0.00257 -0.0865 0.6616 0.2629
-1.750 0.2740 0.00887 0.00252 -0.0859 0.6488 0.2966
-1.500 0.2990 0.00878 0.00248 -0.0851 0.6352 0.3289
-1.250 0.3238 0.00871 0.00245 -0.0844 0.6211 0.3639
-1.000 0.3481 0.00864 0.00243 -0.0835 0.6059 0.4020
-0.750 0.3720 0.00857 0.00243 -0.0826 0.5898 0.4462
-0.500 0.3952 0.00848 0.00243 -0.0815 0.5729 0.5001
-0.250 0.4169 0.00832 0.00245 -0.0802 0.5557 0.5726
0.000 0.4347 0.00803 0.00252 -0.0779 0.5381 0.6984
0.250 0.4526 0.00778 0.00262 -0.0754 0.5200 0.8347
0.500 0.5103 0.00793 0.00279 -0.0814 0.4939 0.9412
0.750 0.5641 0.00819 0.00289 -0.0869 0.4689 0.9726
1.000 0.6066 0.00845 0.00298 -0.0899 0.4483 0.9896
1.250 0.6541 0.00869 0.00306 -0.0942 0.4301 0.9999
1.500 0.6752 0.00886 0.00313 -0.0928 0.4169 1.0000
1.750 0.6959 0.00903 0.00320 -0.0914 0.4066 1.0000
2.000 0.7167 0.00920 0.00329 -0.0899 0.3970 1.0000
2.250 0.7385 0.00936 0.00338 -0.0886 0.3889 1.0000
2.500 0.7598 0.00954 0.00348 -0.0873 0.3815 1.0000
2.750 0.7818 0.00971 0.00360 -0.0861 0.3755 1.0000
3.000 0.8042 0.00986 0.00371 -0.0849 0.3696 1.0000
3.250 0.8256 0.01007 0.00384 -0.0836 0.3637 1.0000
3.500 0.8484 0.01021 0.00397 -0.0826 0.3585 1.0000
3.750 0.8711 0.01037 0.00410 -0.0815 0.3531 1.0000
4.000 0.8927 0.01058 0.00424 -0.0802 0.3481 1.0000
4.250 0.9152 0.01076 0.00440 -0.0791 0.3438 1.0000
4.500 0.9384 0.01090 0.00454 -0.0782 0.3398 1.0000
4.750 0.9609 0.01107 0.00470 -0.0771 0.3357 1.0000
5.000 0.9826 0.01130 0.00488 -0.0759 0.3316 1.0000
5.250 1.0051 0.01150 0.00507 -0.0749 0.3280 1.0000
5.500 1.0284 0.01163 0.00523 -0.0740 0.3243 1.0000
5.750 1.0509 0.01181 0.00541 -0.0730 0.3203 1.0000
6.000 1.0724 0.01204 0.00561 -0.0718 0.3162 1.0000
6.250 1.0942 0.01226 0.00582 -0.0707 0.3120 1.0000
6.500 1.1171 0.01239 0.00599 -0.0697 0.3077 1.0000
6.750 1.1386 0.01258 0.00619 -0.0686 0.3030 1.0000
7.000 1.1586 0.01286 0.00642 -0.0672 0.2982 1.0000
7.250 1.1808 0.01300 0.00662 -0.0661 0.2938 1.0000
7.500 1.2012 0.01318 0.00683 -0.0648 0.2886 1.0000
7.750 1.2188 0.01344 0.00706 -0.0629 0.2832 1.0000
8.000 1.2387 0.01361 0.00728 -0.0615 0.2774 1.0000
8.250 1.2571 0.01383 0.00751 -0.0599 0.2703 1.0000
8.500 1.2752 0.01408 0.00777 -0.0582 0.2621 1.0000
8.750 1.2911 0.01442 0.00805 -0.0562 0.2513 1.0000
9.000 1.3085 0.01474 0.00835 -0.0546 0.2384 1.0000
9.250 1.3238 0.01517 0.00874 -0.0526 0.2245 1.0000
9.500 1.3379 0.01567 0.00918 -0.0506 0.2116 1.0000
9.750 1.3516 0.01622 0.00969 -0.0486 0.2015 1.0000
10.000 1.3635 0.01687 0.01029 -0.0464 0.1935 1.0000
10.250 1.3784 0.01740 0.01084 -0.0446 0.1879 1.0000
10.500 1.3905 0.01808 0.01151 -0.0426 0.1827 1.0000
10.750 1.4034 0.01874 0.01218 -0.0408 0.1786 1.0000
11.000 1.4182 0.01933 0.01281 -0.0392 0.1750 1.0000
11.250 1.4303 0.02007 0.01358 -0.0375 0.1708 1.0000
11.500 1.4394 0.02101 0.01451 -0.0354 0.1668 1.0000
11.750 1.4543 0.02165 0.01522 -0.0342 0.1636 1.0000
12.000 1.4682 0.02237 0.01600 -0.0329 0.1604 1.0000
12.250 1.4795 0.02326 0.01693 -0.0314 0.1571 1.0000
12.500 1.4873 0.02441 0.01810 -0.0297 0.1534 1.0000
12.750 1.5006 0.02525 0.01901 -0.0286 0.1497 1.0000
13.000 1.5142 0.02610 0.01993 -0.0276 0.1456 1.0000
13.250 1.5228 0.02733 0.02118 -0.0263 0.1412 1.0000
13.500 1.5336 0.02845 0.02236 -0.0253 0.1353 1.0000
13.750 1.5430 0.02972 0.02365 -0.0244 0.1282 1.0000
14.000 1.5496 0.03126 0.02518 -0.0234 0.1165 1.0000
14.250 1.5446 0.03386 0.02765 -0.0221 0.0949 1.0000
14.500 1.5269 0.03777 0.03141 -0.0207 0.0715 1.0000
14.750 1.4932 0.04356 0.03708 -0.0196 0.0462 1.0000
15.000 1.4704 0.04865 0.04217 -0.0193 0.0333 1.0000
15.250 1.4519 0.05361 0.04718 -0.0195 0.0270 1.0000
15.500 1.4393 0.05808 0.05173 -0.0199 0.0244 1.0000
15.750 1.4301 0.06229 0.05605 -0.0205 0.0232 1.0000
16.000 1.4181 0.06698 0.06085 -0.0213 0.0221 1.0000
16.250 1.4049 0.07195 0.06592 -0.0224 0.0213 1.0000
16.500 1.3901 0.07728 0.07137 -0.0236 0.0206 1.0000
16.750 1.3787 0.08219 0.07641 -0.0249 0.0202 1.0000
17.000 1.3673 0.08719 0.08152 -0.0262 0.0200 1.0000
17.250 1.3552 0.09239 0.08685 -0.0277 0.0197 1.0000
17.500 1.3408 0.09803 0.09260 -0.0295 0.0192 1.0000
17.750 1.3276 0.10352 0.09821 -0.0313 0.0190 1.0000
18.000 1.3146 0.10908 0.10387 -0.0332 0.0188 1.0000
18.250 1.3002 0.11497 0.10988 -0.0354 0.0185 1.0000
18.500 1.2868 0.12074 0.11575 -0.0377 0.0182 1.0000
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