GOE 525 AIRFOIL (goe525-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 525 AIRFOIL (goe525-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.44 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe525-il-1000000-n5.txt Download as CSV file: xf-goe525-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.0820 0.03976 0.03658 -0.2175 0.8462 0.0233
-11.250 0.0452 0.03425 0.03094 -0.2194 0.8364 0.0233
-11.000 0.0243 0.03053 0.02709 -0.2206 0.8281 0.0233
-10.750 0.0197 0.02675 0.02319 -0.2248 0.8205 0.0233
-10.500 0.0310 0.02369 0.01996 -0.2300 0.8136 0.0234
-10.250 0.0539 0.02132 0.01746 -0.2355 0.8078 0.0235
-10.000 0.0844 0.01894 0.01490 -0.2422 0.8016 0.0236
-9.750 0.1190 0.01716 0.01296 -0.2480 0.7956 0.0239
-9.500 0.1536 0.01598 0.01167 -0.2520 0.7882 0.0241
-9.250 0.1842 0.01523 0.01079 -0.2542 0.7781 0.0242
-9.000 0.2143 0.01463 0.01010 -0.2558 0.7665 0.0244
-8.750 0.2435 0.01414 0.00949 -0.2570 0.7549 0.0246
-8.500 0.2719 0.01371 0.00895 -0.2579 0.7423 0.0248
-8.250 0.3006 0.01334 0.00847 -0.2587 0.7292 0.0250
-8.000 0.3285 0.01302 0.00804 -0.2592 0.7153 0.0252
-7.750 0.3552 0.01277 0.00767 -0.2594 0.6992 0.0255
-7.500 0.3814 0.01255 0.00731 -0.2595 0.6825 0.0258
-7.250 0.4081 0.01232 0.00695 -0.2597 0.6678 0.0260
-7.000 0.4350 0.01212 0.00663 -0.2598 0.6554 0.0262
-6.750 0.4634 0.01190 0.00632 -0.2602 0.6449 0.0264
-6.500 0.4908 0.01173 0.00605 -0.2603 0.6353 0.0266
-6.250 0.5193 0.01156 0.00580 -0.2607 0.6266 0.0268
-6.000 0.5467 0.01143 0.00558 -0.2608 0.6189 0.0270
-5.750 0.5760 0.01127 0.00536 -0.2612 0.6133 0.0272
-5.500 0.6044 0.01113 0.00517 -0.2614 0.6070 0.0273
-5.250 0.6331 0.01094 0.00490 -0.2619 0.6006 0.0277
-5.000 0.6627 0.01077 0.00469 -0.2624 0.5952 0.0281
-4.750 0.6905 0.01066 0.00454 -0.2625 0.5890 0.0285
-4.500 0.7166 0.01061 0.00443 -0.2622 0.5833 0.0288
-4.250 0.7444 0.01052 0.00432 -0.2622 0.5788 0.0292
-4.000 0.7719 0.01045 0.00422 -0.2622 0.5737 0.0297
-3.750 0.7980 0.01043 0.00414 -0.2619 0.5675 0.0301
-3.500 0.8238 0.01042 0.00409 -0.2616 0.5617 0.0307
-3.250 0.8507 0.01040 0.00403 -0.2614 0.5557 0.0312
-3.000 0.8765 0.01041 0.00399 -0.2610 0.5493 0.0316
-2.750 0.9025 0.01041 0.00395 -0.2607 0.5435 0.0324
-2.500 0.9293 0.01041 0.00393 -0.2606 0.5370 0.0332
-2.250 0.9540 0.01048 0.00395 -0.2600 0.5289 0.0340
-2.000 0.9797 0.01054 0.00397 -0.2597 0.5218 0.0351
-1.750 1.0047 0.01063 0.00401 -0.2591 0.5137 0.0361
-1.500 1.0294 0.01073 0.00407 -0.2586 0.5061 0.0382
-1.250 1.0539 0.01084 0.00415 -0.2580 0.4968 0.0409
-1.000 1.0780 0.01097 0.00424 -0.2574 0.4878 0.0473
-0.750 1.1029 0.01107 0.00435 -0.2570 0.4785 0.0643
-0.500 1.1274 0.01118 0.00447 -0.2565 0.4705 0.0868
-0.250 1.1517 0.01130 0.00463 -0.2560 0.4617 0.1176
0.000 1.1748 0.01148 0.00479 -0.2552 0.4538 0.1349
0.250 1.1982 0.01166 0.00495 -0.2545 0.4459 0.1463
0.500 1.2206 0.01189 0.00514 -0.2536 0.4380 0.1594
0.750 1.2448 0.01203 0.00532 -0.2531 0.4306 0.1863
1.000 1.2675 0.01222 0.00559 -0.2525 0.4221 0.2500
1.250 1.2912 0.01238 0.00580 -0.2519 0.4161 0.2854
1.500 1.3142 0.01259 0.00602 -0.2512 0.4101 0.3094
1.750 1.3363 0.01285 0.00627 -0.2503 0.4045 0.3296
2.000 1.3597 0.01304 0.00649 -0.2496 0.4004 0.3487
2.250 1.3828 0.01324 0.00672 -0.2490 0.3966 0.3683
2.750 1.4270 0.01375 0.00727 -0.2473 0.3882 0.4177
3.000 1.4491 0.01402 0.00756 -0.2465 0.3844 0.4413
3.250 1.4721 0.01425 0.00782 -0.2458 0.3809 0.4583
3.500 1.4936 0.01453 0.00811 -0.2449 0.3768 0.4723
3.750 1.5140 0.01488 0.00846 -0.2438 0.3722 0.4850
4.000 1.5340 0.01526 0.00883 -0.2426 0.3676 0.4969
4.250 1.5562 0.01554 0.00913 -0.2419 0.3648 0.5111
4.500 1.5779 0.01584 0.00946 -0.2410 0.3614 0.5238
4.750 1.5981 0.01621 0.00983 -0.2400 0.3576 0.5321
5.000 1.6172 0.01664 0.01026 -0.2388 0.3536 0.5393
5.250 1.6368 0.01706 0.01068 -0.2376 0.3498 0.5482
5.500 1.6575 0.01743 0.01106 -0.2367 0.3454 0.5557
5.750 1.6768 0.01787 0.01151 -0.2356 0.3407 0.5619
6.000 1.6933 0.01847 0.01208 -0.2341 0.3348 0.5681
6.250 1.7125 0.01893 0.01254 -0.2330 0.3301 0.5735
6.500 1.7314 0.01941 0.01304 -0.2319 0.3251 0.5789
6.750 1.7479 0.02004 0.01366 -0.2305 0.3196 0.5839
7.000 1.7652 0.02063 0.01424 -0.2292 0.3154 0.5889
7.250 1.7835 0.02116 0.01480 -0.2281 0.3110 0.5952
7.500 1.8004 0.02180 0.01544 -0.2268 0.3058 0.6032
7.750 1.8149 0.02258 0.01621 -0.2252 0.3009 0.6092
8.000 1.8327 0.02317 0.01684 -0.2241 0.2974 0.6151
8.250 1.8497 0.02384 0.01752 -0.2229 0.2930 0.6214
8.500 1.8637 0.02470 0.01838 -0.2214 0.2878 0.6271
8.750 1.8783 0.02553 0.01922 -0.2200 0.2831 0.6313
9.000 1.8943 0.02630 0.02002 -0.2188 0.2783 0.6355
9.250 1.9072 0.02728 0.02100 -0.2172 0.2729 0.6397
9.500 1.9195 0.02834 0.02205 -0.2156 0.2670 0.6438
9.750 1.9322 0.02940 0.02310 -0.2142 0.2599 0.6479
10.000 1.9411 0.03075 0.02445 -0.2123 0.2529 0.6524
10.250 1.9552 0.03174 0.02547 -0.2111 0.2484 0.6572
10.500 1.9653 0.03306 0.02679 -0.2095 0.2424 0.6615
10.750 1.9745 0.03449 0.02822 -0.2078 0.2363 0.6654
11.000 1.9858 0.03577 0.02953 -0.2065 0.2308 0.6699
11.250 1.9945 0.03731 0.03108 -0.2049 0.2258 0.6750
11.500 2.0041 0.03879 0.03258 -0.2035 0.2211 0.6801
11.750 2.0137 0.04031 0.03413 -0.2022 0.2164 0.6853
12.000 2.0205 0.04211 0.03595 -0.2006 0.2104 0.6908
12.250 2.0269 0.04401 0.03787 -0.1992 0.2052 0.6961
12.500 2.0336 0.04590 0.03978 -0.1978 0.1987 0.7017
12.750 2.0362 0.04827 0.04217 -0.1963 0.1923 0.7083
13.250 2.0403 0.05332 0.04725 -0.1934 0.1758 0.7250
13.500 2.0348 0.05681 0.05072 -0.1918 0.1633 0.7350
13.750 2.0026 0.06366 0.05743 -0.1891 0.1324 0.7414
14.000 1.9674 0.07133 0.06501 -0.1869 0.1040 0.7467
14.250 1.9479 0.07732 0.07100 -0.1859 0.0892 0.7612
14.500 1.9395 0.08150 0.07542 -0.1850 0.0825 0.9353
14.750 1.9338 0.08567 0.07964 -0.1845 0.0780 1.0000
15.000 1.9295 0.08978 0.08380 -0.1842 0.0742 1.0000
15.250 1.9285 0.09344 0.08753 -0.1841 0.0717 1.0000
15.500 1.9256 0.09740 0.09155 -0.1840 0.0684 1.0000
15.750 1.9190 0.10197 0.09617 -0.1841 0.0648 1.0000
16.000 1.9158 0.10603 0.10028 -0.1842 0.0612 1.0000
16.250 1.9077 0.11088 0.10516 -0.1846 0.0561 1.0000
16.500 1.8928 0.11687 0.11115 -0.1852 0.0460 1.0000
16.750 1.8651 0.12502 0.11929 -0.1865 0.0306 1.0000
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