GOE 525 AIRFOIL (goe525-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 525 AIRFOIL (goe525-il) Reynolds number: 100,000 Max Cl/Cd: 50.85 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe525-il-100000-n5.txt Download as CSV file: xf-goe525-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 525 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
------ -------- --------- --------- -------- -------- --------
-9.500 0.1759 0.11221 0.10684 -0.1195 0.8691 0.0729
-9.250 0.1890 0.10932 0.10393 -0.1221 0.8660 0.0751
-9.000 0.1835 0.10801 0.10265 -0.1226 0.8585 0.0768
-8.750 0.1766 0.10667 0.10133 -0.1235 0.8509 0.0774
-8.250 0.2029 0.10045 0.09511 -0.1235 0.8411 0.0790
-8.000 0.2165 0.09817 0.09284 -0.1229 0.8353 0.0813
-7.750 0.2313 0.09537 0.09001 -0.1250 0.8320 0.0840
-7.500 0.2229 0.09435 0.08904 -0.1225 0.8217 0.0855
-7.250 0.2168 0.09253 0.08722 -0.1244 0.8151 0.0875
-6.250 0.1919 0.08082 0.07549 -0.1188 0.7812 0.0596
-6.000 0.2064 0.07712 0.07175 -0.1216 0.7780 0.0594
-5.500 0.1876 0.07398 0.06866 -0.1167 0.7555 0.0591
-5.250 0.1915 0.07129 0.06597 -0.1174 0.7476 0.0587
-4.750 0.3108 0.03967 0.03322 -0.1827 0.7362 0.0537
-4.500 0.3608 0.03710 0.03042 -0.1901 0.7319 0.0553
-4.250 0.4386 0.03282 0.02545 -0.2042 0.7298 0.0570
-4.000 0.5039 0.02995 0.02197 -0.2131 0.7276 0.0582
-3.750 0.5410 0.02878 0.02047 -0.2160 0.7204 0.0592
-3.500 0.5820 0.02763 0.01904 -0.2190 0.7146 0.0606
-3.250 0.6264 0.02658 0.01792 -0.2221 0.7107 0.0632
-3.000 0.6582 0.02609 0.01730 -0.2232 0.7034 0.0659
-2.750 0.6947 0.02543 0.01644 -0.2248 0.6969 0.0682
-2.500 0.7404 0.02450 0.01550 -0.2280 0.6926 0.0713
-2.250 0.7680 0.02434 0.01528 -0.2283 0.6843 0.0747
-2.000 0.8073 0.02382 0.01471 -0.2305 0.6780 0.0813
-1.750 0.8515 0.02323 0.01405 -0.2335 0.6725 0.0921
-1.500 0.8797 0.02316 0.01400 -0.2340 0.6639 0.1062
-1.250 0.9245 0.02267 0.01348 -0.2372 0.6580 0.1453
-1.000 0.9568 0.02256 0.01346 -0.2385 0.6504 0.1889
-0.750 0.9912 0.02246 0.01347 -0.2401 0.6428 0.2495
-0.500 1.0313 0.02232 0.01335 -0.2424 0.6364 0.3149
-0.250 1.0531 0.02260 0.01371 -0.2415 0.6280 0.3557
0.000 1.0880 0.02264 0.01370 -0.2426 0.6215 0.3976
0.250 1.1114 0.02294 0.01400 -0.2418 0.6137 0.4263
0.500 1.1365 0.02320 0.01420 -0.2413 0.6060 0.4524
0.750 1.1695 0.02333 0.01421 -0.2421 0.5997 0.4763
1.000 1.1849 0.02382 0.01471 -0.2400 0.5912 0.4951
1.250 1.2130 0.02404 0.01483 -0.2399 0.5844 0.5156
1.500 1.2340 0.02444 0.01519 -0.2387 0.5770 0.5346
1.750 1.2533 0.02487 0.01559 -0.2372 0.5693 0.5538
2.250 1.2946 0.02567 0.01633 -0.2347 0.5551 0.5886
2.500 1.3169 0.02600 0.01660 -0.2338 0.5483 0.6029
2.750 1.3389 0.02638 0.01692 -0.2329 0.5416 0.6154
3.000 1.3554 0.02691 0.01743 -0.2312 0.5339 0.6276
3.250 1.3807 0.02715 0.01756 -0.2308 0.5280 0.6385
3.500 1.3954 0.02776 0.01819 -0.2290 0.5207 0.6492
3.750 1.4139 0.02822 0.01861 -0.2276 0.5138 0.6597
4.000 1.4379 0.02852 0.01881 -0.2271 0.5080 0.6703
4.250 1.4505 0.02926 0.01958 -0.2250 0.5007 0.6808
4.500 1.4704 0.02967 0.01995 -0.2239 0.4946 0.6905
4.750 1.4897 0.03018 0.02041 -0.2229 0.4886 0.7009
5.000 1.5033 0.03090 0.02116 -0.2210 0.4818 0.7114
5.250 1.5241 0.03131 0.02152 -0.2201 0.4762 0.7229
5.500 1.5406 0.03195 0.02217 -0.2187 0.4703 0.7350
5.750 1.5540 0.03274 0.02300 -0.2169 0.4640 0.7476
6.000 1.5742 0.03319 0.02341 -0.2160 0.4588 0.7605
6.250 1.5917 0.03382 0.02406 -0.2149 0.4536 0.7724
6.500 1.6028 0.03476 0.02509 -0.2129 0.4476 0.7846
6.750 1.6202 0.03537 0.02571 -0.2118 0.4425 0.7999
7.000 1.6428 0.03567 0.02601 -0.2112 0.4381 0.8230
7.250 1.6443 0.03681 0.02736 -0.2080 0.4323 1.0000
7.500 1.6587 0.03784 0.02838 -0.2068 0.4269 1.0000
7.750 1.6818 0.03840 0.02886 -0.2065 0.4225 1.0000
8.000 1.6947 0.03956 0.03006 -0.2052 0.4176 1.0000
8.250 1.7029 0.04100 0.03159 -0.2033 0.4124 1.0000
8.500 1.7183 0.04201 0.03260 -0.2022 0.4078 1.0000
8.750 1.7425 0.04249 0.03300 -0.2021 0.4040 1.0000
9.000 1.7467 0.04424 0.03487 -0.2000 0.3990 1.0000
9.250 1.7518 0.04596 0.03669 -0.1980 0.3937 1.0000
9.500 1.7656 0.04708 0.03782 -0.1968 0.3892 1.0000
9.750 1.7912 0.04741 0.03806 -0.1968 0.3856 1.0000
10.000 1.7838 0.05014 0.04100 -0.1939 0.3802 1.0000
10.250 1.7867 0.05217 0.04315 -0.1920 0.3754 1.0000
10.500 1.8002 0.05340 0.04440 -0.1910 0.3714 1.0000
10.750 1.8242 0.05380 0.04474 -0.1908 0.3683 1.0000
11.000 1.8134 0.05716 0.04832 -0.1881 0.3634 1.0000
11.250 1.8099 0.06001 0.05133 -0.1861 0.3587 1.0000
11.500 1.8197 0.06165 0.05303 -0.1851 0.3549 1.0000
11.750 1.8405 0.06225 0.05361 -0.1847 0.3518 1.0000
12.000 1.8301 0.06597 0.05751 -0.1827 0.3471 1.0000
12.250 1.8124 0.07064 0.06239 -0.1806 0.3417 1.0000
12.500 1.8210 0.07246 0.06427 -0.1798 0.3376 1.0000
12.750 1.8457 0.07244 0.06420 -0.1795 0.3344 1.0000
13.000 1.8006 0.08084 0.07293 -0.1773 0.3281 1.0000
13.250 1.7856 0.08589 0.07814 -0.1764 0.3229 1.0000
13.500 1.8035 0.08659 0.07885 -0.1760 0.3198 1.0000
13.750 1.8330 0.08577 0.07801 -0.1757 0.3175 1.0000
14.000 1.7022 0.10813 0.10091 -0.1762 0.3056 1.0000
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Polar data table (+)
Polar graphs
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