GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 529 AIRFOIL (goe529-il) Reynolds number: 200,000 Max Cl/Cd: 81.39 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe529-il-200000.txt Download as CSV file: xf-goe529-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 529 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2433 0.10115 0.09789 -0.0361 1.0000 0.0398
-8.500 -0.2506 0.09967 0.09650 -0.0349 1.0000 0.0411
-8.250 -0.2677 0.09934 0.09629 -0.0317 1.0000 0.0416
-8.000 -0.2553 0.09650 0.09348 -0.0452 0.9883 0.0426
-7.750 -0.2343 0.09022 0.08720 -0.0528 0.9801 0.0432
-7.500 -0.2107 0.08574 0.08271 -0.0509 0.9778 0.0442
-7.250 -0.1834 0.08198 0.07893 -0.0545 0.9720 0.0468
-7.000 -0.1570 0.07767 0.07460 -0.0625 0.9606 0.0503
-6.750 -0.1082 0.07119 0.06795 -0.0890 0.9443 0.0531
-6.500 -0.0942 0.06639 0.06320 -0.0859 0.9377 0.0544
-6.250 -0.0686 0.06321 0.05998 -0.0874 0.9277 0.0563
-6.000 -0.0414 0.05975 0.05645 -0.0922 0.9128 0.0600
-5.750 -0.0073 0.05423 0.05055 -0.1061 0.8904 0.0654
-5.500 0.0063 0.05132 0.04766 -0.1042 0.8751 0.0668
-5.250 0.0234 0.04914 0.04539 -0.1037 0.8587 0.0688
-5.000 0.0433 0.04672 0.04283 -0.1049 0.8432 0.0723
-4.750 0.0730 0.04238 0.03797 -0.1109 0.8291 0.0793
-4.500 0.0891 0.04031 0.03594 -0.1097 0.8177 0.0814
-4.250 0.1095 0.03851 0.03403 -0.1095 0.8068 0.0849
-4.000 0.1384 0.03547 0.03044 -0.1123 0.7959 0.0940
-3.750 0.1585 0.03329 0.02825 -0.1119 0.7872 0.0959
-3.500 0.1808 0.03178 0.02665 -0.1116 0.7779 0.1002
-3.250 0.2066 0.02970 0.02422 -0.1123 0.7695 0.1106
-3.000 0.2377 0.02418 0.01779 -0.1123 0.7626 0.0769
-2.750 0.2627 0.02031 0.01331 -0.1119 0.7557 0.0680
-2.500 0.2888 0.01922 0.01198 -0.1115 0.7480 0.0694
-2.250 0.3156 0.01790 0.01031 -0.1110 0.7411 0.0693
-2.000 0.3425 0.01686 0.00900 -0.1105 0.7338 0.0695
-1.750 0.3696 0.01613 0.00807 -0.1101 0.7273 0.0708
-1.500 0.3963 0.01552 0.00734 -0.1096 0.7197 0.0729
-1.250 0.4238 0.01516 0.00681 -0.1092 0.7135 0.0768
-1.000 0.4497 0.01454 0.00616 -0.1087 0.7060 0.0808
-0.750 0.4768 0.01416 0.00574 -0.1084 0.6999 0.0868
-0.500 0.5023 0.01377 0.00538 -0.1078 0.6922 0.0966
-0.250 0.5291 0.01349 0.00510 -0.1073 0.6857 0.1209
0.000 0.5545 0.01327 0.00502 -0.1069 0.6782 0.1574
0.250 0.5809 0.01309 0.00490 -0.1065 0.6714 0.1941
0.500 0.6054 0.01279 0.00489 -0.1059 0.6638 0.2697
0.750 0.6541 0.01118 0.00480 -0.1101 0.6563 1.0000
1.000 0.6793 0.01135 0.00484 -0.1095 0.6484 1.0000
1.250 0.7055 0.01151 0.00483 -0.1090 0.6409 1.0000
1.500 0.7305 0.01168 0.00493 -0.1083 0.6325 1.0000
1.750 0.7568 0.01185 0.00495 -0.1078 0.6249 1.0000
2.000 0.7813 0.01201 0.00507 -0.1071 0.6157 1.0000
2.250 0.8078 0.01218 0.00509 -0.1067 0.6079 1.0000
2.500 0.8320 0.01231 0.00522 -0.1059 0.5981 1.0000
2.750 0.8577 0.01248 0.00531 -0.1054 0.5901 1.0000
3.000 0.8828 0.01262 0.00541 -0.1048 0.5814 1.0000
3.250 0.9078 0.01278 0.00553 -0.1042 0.5728 1.0000
3.500 0.9333 0.01290 0.00559 -0.1036 0.5642 1.0000
3.750 0.9576 0.01302 0.00573 -0.1029 0.5544 1.0000
4.000 0.9831 0.01314 0.00578 -0.1023 0.5462 1.0000
4.250 1.0074 0.01326 0.00593 -0.1016 0.5365 1.0000
4.500 1.0321 0.01341 0.00608 -0.1010 0.5280 1.0000
4.750 1.0571 0.01354 0.00618 -0.1004 0.5194 1.0000
5.000 1.0812 0.01371 0.00637 -0.0997 0.5098 1.0000
5.250 1.1062 0.01388 0.00652 -0.0991 0.5018 1.0000
5.500 1.1301 0.01407 0.00675 -0.0984 0.4924 1.0000
5.750 1.1543 0.01429 0.00697 -0.0978 0.4836 1.0000
6.000 1.1787 0.01451 0.00718 -0.0972 0.4750 1.0000
6.250 1.2021 0.01477 0.00750 -0.0964 0.4655 1.0000
6.500 1.2265 0.01507 0.00777 -0.0958 0.4576 1.0000
6.750 1.2496 0.01536 0.00812 -0.0951 0.4486 1.0000
7.000 1.2729 0.01569 0.00849 -0.0943 0.4396 1.0000
7.250 1.2955 0.01600 0.00877 -0.0935 0.4289 1.0000
7.500 1.3159 0.01628 0.00905 -0.0922 0.4155 1.0000
7.750 1.3353 0.01656 0.00938 -0.0908 0.4017 1.0000
8.000 1.3543 0.01686 0.00975 -0.0893 0.3878 1.0000
8.250 1.3732 0.01719 0.01013 -0.0879 0.3748 1.0000
8.500 1.3913 0.01752 0.01053 -0.0863 0.3610 1.0000
8.750 1.4084 0.01789 0.01094 -0.0846 0.3464 1.0000
9.000 1.4242 0.01829 0.01140 -0.0827 0.3310 1.0000
9.250 1.4381 0.01875 0.01189 -0.0805 0.3141 1.0000
9.500 1.4492 0.01930 0.01244 -0.0779 0.2932 1.0000
9.750 1.4525 0.02006 0.01311 -0.0741 0.2671 1.0000
10.000 1.4532 0.02105 0.01399 -0.0702 0.2381 1.0000
10.250 1.4502 0.02238 0.01517 -0.0661 0.2024 1.0000
10.500 1.4373 0.02448 0.01694 -0.0615 0.1480 1.0000
10.750 1.4220 0.02710 0.01927 -0.0574 0.1153 1.0000
11.000 1.4064 0.03010 0.02204 -0.0540 0.0686 1.0000
11.250 1.3892 0.03354 0.02529 -0.0512 0.0494 1.0000
11.500 1.3813 0.03649 0.02828 -0.0493 0.0412 1.0000
11.750 1.3760 0.03939 0.03126 -0.0480 0.0371 1.0000
12.000 1.3745 0.04206 0.03405 -0.0470 0.0342 1.0000
12.250 1.3695 0.04520 0.03728 -0.0462 0.0322 1.0000
12.500 1.3620 0.04874 0.04093 -0.0457 0.0310 1.0000
12.750 1.3562 0.05223 0.04454 -0.0453 0.0299 1.0000
13.000 1.3522 0.05557 0.04802 -0.0450 0.0293 1.0000
13.250 1.3475 0.05912 0.05169 -0.0449 0.0284 1.0000
13.500 1.3429 0.06274 0.05542 -0.0450 0.0277 1.0000
13.750 1.3387 0.06639 0.05917 -0.0451 0.0271 1.0000
14.000 1.3351 0.07002 0.06289 -0.0453 0.0263 1.0000
14.250 1.3321 0.07364 0.06658 -0.0456 0.0256 1.0000
14.500 1.3290 0.07718 0.07016 -0.0457 0.0249 1.0000
14.750 1.3295 0.07996 0.07293 -0.0449 0.0241 1.0000
15.000 1.3340 0.08267 0.07576 -0.0450 0.0235 1.0000
15.250 1.3405 0.08493 0.07812 -0.0445 0.0231 1.0000
15.500 1.3483 0.08704 0.08032 -0.0439 0.0226 1.0000
15.750 1.3571 0.08907 0.08245 -0.0433 0.0222 1.0000
16.000 1.3657 0.09123 0.08474 -0.0426 0.0219 1.0000
16.250 1.3735 0.09359 0.08727 -0.0422 0.0218 1.0000
16.500 1.3790 0.09642 0.09026 -0.0420 0.0216 1.0000
16.750 1.3816 0.09977 0.09380 -0.0423 0.0214 1.0000
17.000 1.3812 0.10361 0.09782 -0.0431 0.0211 1.0000
17.250 1.3791 0.10773 0.10212 -0.0443 0.0209 1.0000
17.500 1.3753 0.11216 0.10673 -0.0457 0.0207 1.0000
17.750 1.3718 0.11653 0.11125 -0.0474 0.0203 1.0000
18.000 1.3643 0.12180 0.11672 -0.0497 0.0202 1.0000
18.250 1.3519 0.12813 0.12330 -0.0528 0.0204 1.0000
18.500 1.3359 0.13538 0.13080 -0.0568 0.0205 1.0000
18.750 1.3158 0.14379 0.13950 -0.0618 0.0209 1.0000
19.000 1.2945 0.15283 0.14879 -0.0675 0.0212 1.0000
19.250 1.2727 0.16246 0.15864 -0.0738 0.0216 1.0000
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