GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 504 AIRFOIL (goe504-il) Reynolds number: 100,000 Max Cl/Cd: 43.56 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe504-il-100000-n5.txt Download as CSV file: xf-goe504-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 504 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1956 0.09527 0.09052 -0.0912 0.9579 0.0389
-11.250 -0.3402 0.06085 0.05560 -0.1200 0.9454 0.0350
-11.000 -0.3611 0.05512 0.04959 -0.1257 0.9325 0.0350
-10.750 -0.3710 0.05163 0.04589 -0.1272 0.9206 0.0353
-10.500 -0.3684 0.04884 0.04293 -0.1281 0.9123 0.0359
-10.250 -0.3720 0.04649 0.04036 -0.1266 0.9007 0.0364
-10.000 -0.3750 0.04416 0.03778 -0.1248 0.8893 0.0368
-9.750 -0.3651 0.04147 0.03476 -0.1248 0.8830 0.0374
-9.500 -0.3632 0.03974 0.03277 -0.1223 0.8717 0.0383
-9.250 -0.3536 0.03782 0.03050 -0.1209 0.8637 0.0394
-9.000 -0.3424 0.03600 0.02828 -0.1193 0.8555 0.0406
-8.750 -0.3273 0.03427 0.02625 -0.1181 0.8479 0.0415
-8.500 -0.3067 0.03265 0.02454 -0.1176 0.8409 0.0424
-8.250 -0.2818 0.03126 0.02304 -0.1178 0.8355 0.0438
-8.000 -0.2660 0.03031 0.02196 -0.1161 0.8268 0.0454
-7.750 -0.2381 0.02901 0.02046 -0.1165 0.8219 0.0471
-7.500 -0.2224 0.02818 0.01947 -0.1145 0.8129 0.0481
-7.250 -0.1966 0.02705 0.01825 -0.1144 0.8073 0.0494
-7.000 -0.1800 0.02634 0.01753 -0.1128 0.7994 0.0512
-6.750 -0.1575 0.02559 0.01669 -0.1121 0.7929 0.0532
-6.500 -0.1360 0.02491 0.01590 -0.1111 0.7863 0.0551
-6.250 -0.1175 0.02434 0.01519 -0.1095 0.7787 0.0567
-6.000 -0.0911 0.02357 0.01431 -0.1095 0.7738 0.0588
-5.750 -0.0770 0.02320 0.01387 -0.1071 0.7649 0.0614
-5.500 -0.0510 0.02264 0.01317 -0.1069 0.7593 0.0660
-5.250 -0.0323 0.02218 0.01268 -0.1054 0.7520 0.0711
-5.000 -0.0094 0.02170 0.01208 -0.1045 0.7453 0.0791
-4.750 0.0163 0.02101 0.01136 -0.1042 0.7400 0.0966
-4.500 0.0313 0.02045 0.01099 -0.1022 0.7321 0.1296
-4.250 0.0566 0.01992 0.01078 -0.1019 0.7266 0.2150
-4.000 0.0773 0.01990 0.01075 -0.1006 0.7194 0.2530
-3.750 0.1023 0.01985 0.01061 -0.1001 0.7129 0.2786
-3.500 0.1314 0.01974 0.01036 -0.1002 0.7078 0.2959
-3.250 0.1498 0.01979 0.01035 -0.0985 0.6999 0.3115
-3.000 0.1780 0.01966 0.01013 -0.0985 0.6945 0.3289
-2.750 0.1993 0.01966 0.01009 -0.0973 0.6878 0.3448
-2.500 0.2227 0.01960 0.00999 -0.0965 0.6813 0.3621
-2.250 0.2528 0.01941 0.00976 -0.0969 0.6765 0.3808
-2.000 0.2693 0.01946 0.00983 -0.0949 0.6686 0.3955
-1.750 0.2965 0.01932 0.00965 -0.0947 0.6631 0.4114
-1.500 0.3198 0.01924 0.00959 -0.0939 0.6569 0.4266
-1.250 0.3422 0.01919 0.00955 -0.0929 0.6502 0.4409
-1.000 0.3725 0.01902 0.00934 -0.0933 0.6453 0.4601
-0.750 0.3907 0.01905 0.00944 -0.0916 0.6381 0.4821
-0.500 0.4164 0.01890 0.00938 -0.0912 0.6322 0.5171
-0.250 0.4431 0.01871 0.00933 -0.0910 0.6270 0.5709
0.000 0.4602 0.01861 0.00953 -0.0889 0.6199 0.6453
0.250 0.4967 0.01838 0.00959 -0.0900 0.6146 0.7622
0.500 0.5576 0.01853 0.00988 -0.0963 0.6077 0.8722
0.750 0.6140 0.01870 0.00996 -0.1020 0.6009 0.9273
1.000 0.6637 0.01885 0.00996 -0.1064 0.5951 0.9585
1.250 0.7046 0.01912 0.01015 -0.1095 0.5876 0.9832
1.500 0.7574 0.01921 0.01008 -0.1148 0.5819 1.0000
1.750 0.7674 0.01946 0.01028 -0.1118 0.5752 1.0000
2.000 0.7837 0.01961 0.01034 -0.1098 0.5691 1.0000
2.250 0.8037 0.01973 0.01035 -0.1085 0.5639 1.0000
2.500 0.8136 0.02002 0.01062 -0.1054 0.5571 1.0000
2.750 0.8334 0.02016 0.01065 -0.1040 0.5516 1.0000
3.000 0.8483 0.02040 0.01085 -0.1018 0.5458 1.0000
3.250 0.8616 0.02066 0.01107 -0.0994 0.5394 1.0000
3.500 0.8847 0.02078 0.01108 -0.0986 0.5343 1.0000
3.750 0.8938 0.02113 0.01144 -0.0954 0.5278 1.0000
4.000 0.9098 0.02137 0.01163 -0.0934 0.5218 1.0000
4.250 0.9319 0.02153 0.01170 -0.0924 0.5167 1.0000
4.500 0.9383 0.02194 0.01216 -0.0888 0.5098 1.0000
4.750 0.9571 0.02214 0.01229 -0.0873 0.5041 1.0000
5.000 0.9700 0.02245 0.01258 -0.0848 0.4985 1.0000
5.250 0.9782 0.02282 0.01295 -0.0815 0.4920 1.0000
5.500 1.0010 0.02298 0.01304 -0.0807 0.4867 1.0000
5.750 1.0053 0.02348 0.01359 -0.0769 0.4801 1.0000
6.000 1.0195 0.02383 0.01392 -0.0748 0.4741 1.0000
6.250 1.0399 0.02408 0.01413 -0.0738 0.4689 1.0000
6.500 1.0441 0.02469 0.01481 -0.0703 0.4621 1.0000
6.750 1.0626 0.02500 0.01509 -0.0690 0.4566 1.0000
7.000 1.0744 0.02551 0.01562 -0.0668 0.4507 1.0000
7.250 1.0837 0.02611 0.01627 -0.0643 0.4442 1.0000
7.500 1.1063 0.02634 0.01644 -0.0637 0.4392 1.0000
7.750 1.1094 0.02720 0.01740 -0.0605 0.4326 1.0000
8.000 1.1229 0.02774 0.01796 -0.0588 0.4267 1.0000
8.250 1.1418 0.02813 0.01834 -0.0578 0.4216 1.0000
8.500 1.1440 0.02917 0.01948 -0.0548 0.4150 1.0000
8.750 1.1609 0.02964 0.01995 -0.0537 0.4096 1.0000
9.000 1.1718 0.03042 0.02079 -0.0519 0.4041 1.0000
9.250 1.1776 0.03146 0.02191 -0.0497 0.3981 1.0000
9.500 1.1970 0.03187 0.02233 -0.0489 0.3933 1.0000
9.750 1.2013 0.03307 0.02361 -0.0467 0.3873 1.0000
10.000 1.2082 0.03415 0.02477 -0.0448 0.3814 1.0000
10.250 1.2306 0.03442 0.02503 -0.0444 0.3770 1.0000
10.500 1.2273 0.03619 0.02695 -0.0419 0.3709 1.0000
10.750 1.2358 0.03729 0.02811 -0.0404 0.3653 1.0000
11.000 1.2535 0.03777 0.02859 -0.0396 0.3599 1.0000
11.250 1.2426 0.04010 0.03106 -0.0369 0.3519 1.0000
11.500 1.2533 0.04089 0.03181 -0.0356 0.3441 1.0000
11.750 1.2427 0.04343 0.03447 -0.0334 0.3356 1.0000
12.000 1.2489 0.04470 0.03576 -0.0321 0.3280 1.0000
12.250 1.2414 0.04730 0.03848 -0.0304 0.3202 1.0000
12.500 1.2523 0.04834 0.03952 -0.0296 0.3139 1.0000
12.750 1.2413 0.05157 0.04290 -0.0282 0.3070 1.0000
13.000 1.2484 0.05294 0.04425 -0.0273 0.2990 1.0000
13.250 1.2343 0.05675 0.04823 -0.0263 0.2917 1.0000
13.500 1.2390 0.05849 0.04996 -0.0256 0.2836 1.0000
13.750 1.2261 0.06250 0.05414 -0.0250 0.2772 1.0000
14.000 1.2335 0.06406 0.05569 -0.0245 0.2696 1.0000
14.250 1.2163 0.06887 0.06070 -0.0242 0.2634 1.0000
14.500 1.2194 0.07104 0.06288 -0.0239 0.2553 1.0000
14.750 1.1998 0.07642 0.06844 -0.0241 0.2480 1.0000
15.000 1.1993 0.07919 0.07120 -0.0240 0.2390 1.0000
15.250 1.1808 0.08473 0.07692 -0.0246 0.2316 1.0000
15.500 1.1796 0.08779 0.08001 -0.0248 0.2235 1.0000
15.750 1.1640 0.09314 0.08552 -0.0255 0.2170 1.0000
16.000 1.1571 0.09719 0.08963 -0.0261 0.2075 1.0000
16.250 1.1467 0.10188 0.09440 -0.0270 0.1984 1.0000
16.500 1.1322 0.10736 0.10003 -0.0281 0.1898 1.0000
16.750 1.1231 0.11200 0.10472 -0.0292 0.1789 1.0000
17.000 1.1131 0.11687 0.10965 -0.0305 0.1665 1.0000
17.250 1.1059 0.12118 0.11384 -0.0316 0.1401 1.0000
17.500 1.0917 0.12640 0.11863 -0.0331 0.0996 1.0000
17.750 1.0741 0.13254 0.12460 -0.0351 0.0677 1.0000
18.000 1.0508 0.13984 0.13169 -0.0377 0.0463 1.0000
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