GOE 525 AIRFOIL (goe525-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 525 AIRFOIL (goe525-il) Reynolds number: 500,000 Max Cl/Cd: 102.14 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe525-il-500000.txt Download as CSV file: xf-goe525-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 0.3305 0.10439 0.10170 -0.1667 0.9428 0.0299
-13.000 0.3246 0.09989 0.09718 -0.1721 0.9416 0.0316
-12.750 0.3294 0.09773 0.09503 -0.1702 0.9357 0.0317
-12.500 0.3486 0.09512 0.09242 -0.1710 0.9331 0.0320
-12.250 0.3645 0.09244 0.08973 -0.1729 0.9309 0.0323
-12.000 0.3807 0.08969 0.08696 -0.1752 0.9290 0.0329
-11.750 0.3961 0.08668 0.08393 -0.1778 0.9271 0.0337
-11.500 0.4040 0.08419 0.08144 -0.1786 0.9230 0.0346
-11.250 0.3889 0.08001 0.07725 -0.1808 0.9168 0.0363
-11.000 0.4106 0.07748 0.07469 -0.1816 0.9139 0.0366
-10.750 0.4301 0.07495 0.07214 -0.1835 0.9111 0.0370
-10.500 0.4378 0.07308 0.07027 -0.1831 0.9053 0.0376
-10.250 0.4103 0.08297 0.08006 -0.1906 0.9238 0.0372
-10.000 0.4182 0.08126 0.07836 -0.1903 0.9172 0.0377
-9.750 0.4356 0.07875 0.07582 -0.1930 0.9131 0.0388
-9.500 0.4212 0.07404 0.07109 -0.1978 0.9042 0.0413
-9.250 0.4383 0.07207 0.06910 -0.1979 0.8984 0.0416
-9.000 0.4671 0.07028 0.06724 -0.2001 0.8940 0.0421
-8.750 0.4717 0.06916 0.06614 -0.1981 0.8859 0.0427
-8.500 0.4863 0.06725 0.06420 -0.1994 0.8799 0.0437
-8.250 0.4933 0.06531 0.06224 -0.1998 0.8729 0.0448
-8.000 0.4747 0.06029 0.05719 -0.2030 0.8628 0.0472
-7.750 0.4870 0.05923 0.05612 -0.2018 0.8562 0.0475
-7.500 0.4980 0.05811 0.05500 -0.2007 0.8488 0.0480
-7.250 0.5108 0.05666 0.05351 -0.2009 0.8418 0.0486
-7.000 0.5135 0.05537 0.05222 -0.1993 0.8327 0.0495
-6.750 0.4462 0.02168 0.01723 -0.2508 0.8117 0.0410
-6.500 0.4776 0.01944 0.01473 -0.2543 0.8040 0.0408
-6.250 0.5126 0.01783 0.01281 -0.2574 0.7965 0.0408
-6.000 0.5452 0.01674 0.01147 -0.2593 0.7888 0.0410
-5.750 0.5770 0.01557 0.01008 -0.2610 0.7800 0.0415
-5.500 0.6060 0.01470 0.00913 -0.2618 0.7708 0.0422
-5.250 0.6352 0.01412 0.00843 -0.2623 0.7608 0.0426
-5.000 0.6625 0.01365 0.00788 -0.2624 0.7498 0.0431
-4.750 0.6909 0.01326 0.00737 -0.2627 0.7392 0.0437
-4.500 0.7180 0.01294 0.00694 -0.2627 0.7271 0.0443
-4.250 0.7447 0.01266 0.00657 -0.2625 0.7149 0.0450
-4.000 0.7717 0.01245 0.00624 -0.2624 0.7032 0.0457
-3.750 0.7983 0.01230 0.00597 -0.2622 0.6917 0.0465
-3.500 0.8262 0.01203 0.00565 -0.2624 0.6813 0.0477
-3.250 0.8537 0.01192 0.00546 -0.2625 0.6717 0.0493
-3.000 0.8808 0.01183 0.00533 -0.2625 0.6622 0.0508
-2.750 0.9080 0.01181 0.00520 -0.2624 0.6535 0.0524
-2.500 0.9362 0.01169 0.00504 -0.2627 0.6451 0.0546
-2.250 0.9638 0.01170 0.00497 -0.2627 0.6374 0.0578
-2.000 0.9916 0.01163 0.00488 -0.2628 0.6303 0.0628
-1.750 1.0192 0.01160 0.00482 -0.2629 0.6227 0.0751
-1.500 1.0485 0.01145 0.00485 -0.2635 0.6157 0.1378
-1.250 1.0737 0.01147 0.00489 -0.2631 0.6084 0.1672
-1.000 1.0992 0.01156 0.00496 -0.2628 0.6015 0.1950
-0.750 1.1240 0.01155 0.00506 -0.2624 0.5948 0.2383
-0.500 1.1477 0.01163 0.00518 -0.2617 0.5874 0.2816
0.000 1.1942 0.01185 0.00545 -0.2600 0.5732 0.3442
0.250 1.2166 0.01202 0.00563 -0.2591 0.5659 0.3786
0.500 1.2393 0.01215 0.00582 -0.2581 0.5586 0.4137
0.750 1.2604 0.01234 0.00603 -0.2569 0.5506 0.4435
1.000 1.2814 0.01256 0.00624 -0.2556 0.5430 0.4654
1.250 1.3022 0.01277 0.00645 -0.2543 0.5346 0.4836
1.500 1.3216 0.01306 0.00669 -0.2528 0.5264 0.5004
1.750 1.3417 0.01331 0.00693 -0.2514 0.5175 0.5166
2.000 1.3603 0.01365 0.00722 -0.2498 0.5091 0.5307
2.250 1.3804 0.01392 0.00749 -0.2484 0.5003 0.5425
2.500 1.3981 0.01432 0.00781 -0.2467 0.4922 0.5551
2.750 1.4186 0.01461 0.00811 -0.2455 0.4844 0.5654
3.000 1.4370 0.01502 0.00845 -0.2439 0.4769 0.5750
3.250 1.4572 0.01535 0.00879 -0.2427 0.4703 0.5841
3.500 1.4765 0.01574 0.00914 -0.2413 0.4636 0.5934
3.750 1.4943 0.01620 0.00956 -0.2397 0.4573 0.6017
4.000 1.5154 0.01653 0.00989 -0.2387 0.4515 0.6109
4.250 1.5340 0.01695 0.01031 -0.2373 0.4454 0.6179
4.500 1.5516 0.01747 0.01077 -0.2358 0.4397 0.6259
4.750 1.5725 0.01780 0.01114 -0.2348 0.4348 0.6318
5.000 1.5919 0.01822 0.01156 -0.2336 0.4296 0.6380
5.250 1.6097 0.01876 0.01204 -0.2322 0.4246 0.6448
5.500 1.6289 0.01920 0.01251 -0.2310 0.4202 0.6505
5.750 1.6487 0.01961 0.01296 -0.2300 0.4157 0.6565
6.000 1.6673 0.02011 0.01344 -0.2288 0.4111 0.6626
6.250 1.6843 0.02070 0.01401 -0.2274 0.4065 0.6679
6.500 1.7031 0.02119 0.01453 -0.2262 0.4024 0.6742
6.750 1.7218 0.02168 0.01506 -0.2251 0.3979 0.6812
7.000 1.7384 0.02227 0.01566 -0.2237 0.3929 0.6885
7.250 1.7533 0.02303 0.01638 -0.2221 0.3876 0.6968
7.500 1.7713 0.02353 0.01697 -0.2210 0.3833 0.7040
7.750 1.7885 0.02413 0.01760 -0.2197 0.3787 0.7108
8.000 1.8043 0.02484 0.01831 -0.2184 0.3743 0.7166
8.250 1.8189 0.02565 0.01913 -0.2169 0.3698 0.7232
8.500 1.8365 0.02625 0.01980 -0.2158 0.3658 0.7306
8.750 1.8525 0.02696 0.02057 -0.2146 0.3610 0.7377
9.000 1.8657 0.02788 0.02149 -0.2131 0.3564 0.7455
9.250 1.8803 0.02876 0.02241 -0.2118 0.3521 0.7542
9.500 1.8973 0.02949 0.02323 -0.2108 0.3478 0.7656
9.750 1.9113 0.03043 0.02424 -0.2095 0.3429 0.7810
10.000 1.9225 0.03149 0.02537 -0.2079 0.3380 0.8199
10.250 1.9336 0.03230 0.02632 -0.2061 0.3336 1.0000
10.500 1.9468 0.03336 0.02742 -0.2048 0.3283 1.0000
10.750 1.9567 0.03471 0.02874 -0.2033 0.3228 1.0000
11.000 1.9674 0.03602 0.03007 -0.2018 0.3177 1.0000
11.250 1.9800 0.03720 0.03130 -0.2006 0.3125 1.0000
11.500 1.9885 0.03874 0.03284 -0.1991 0.3073 1.0000
11.750 1.9972 0.04029 0.03440 -0.1976 0.3025 1.0000
12.000 2.0090 0.04161 0.03579 -0.1965 0.2978 1.0000
12.250 2.0169 0.04329 0.03749 -0.1951 0.2926 1.0000
12.500 2.0216 0.04531 0.03951 -0.1935 0.2874 1.0000
12.750 2.0325 0.04679 0.04106 -0.1925 0.2826 1.0000
13.000 2.0394 0.04869 0.04298 -0.1913 0.2776 1.0000
13.250 2.0429 0.05095 0.04525 -0.1898 0.2729 1.0000
13.500 2.0518 0.05271 0.04709 -0.1888 0.2691 1.0000
13.750 2.0593 0.05465 0.04909 -0.1878 0.2646 1.0000
14.000 2.0625 0.05708 0.05155 -0.1867 0.2600 1.0000
14.250 2.0656 0.05957 0.05407 -0.1856 0.2555 1.0000
14.500 2.0719 0.06176 0.05634 -0.1848 0.2507 1.0000
14.750 2.0739 0.06446 0.05908 -0.1838 0.2458 1.0000
15.000 2.0730 0.06756 0.06220 -0.1828 0.2410 1.0000
15.250 2.0788 0.06991 0.06465 -0.1822 0.2368 1.0000
15.500 2.0802 0.07282 0.06762 -0.1815 0.2318 1.0000
15.750 2.0762 0.07646 0.07127 -0.1807 0.2268 1.0000
16.000 2.0790 0.07927 0.07418 -0.1803 0.2217 1.0000
16.250 2.0756 0.08292 0.07788 -0.1797 0.2156 1.0000
16.500 2.0713 0.08675 0.08175 -0.1793 0.2100 1.0000
16.750 2.0682 0.09047 0.08555 -0.1790 0.2031 1.0000
17.000 2.0590 0.09508 0.09019 -0.1788 0.1967 1.0000
17.250 2.0525 0.09935 0.09451 -0.1788 0.1873 1.0000
17.500 2.0407 0.10443 0.09962 -0.1789 0.1770 1.0000
17.750 2.0212 0.11076 0.10594 -0.1794 0.1624 1.0000
18.000 1.9924 0.11861 0.11375 -0.1804 0.1439 1.0000
18.250 1.9546 0.12798 0.12304 -0.1821 0.1210 1.0000
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