GOE 531 AIRFOIL (goe531-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 531 AIRFOIL (goe531-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.71 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe531-il-1000000-n5.txt Download as CSV file: xf-goe531-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 531 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
------ -------- --------- --------- -------- -------- --------
-11.750 0.6217 0.09261 0.08837 -0.2417 0.6607 0.0207
-11.500 0.6305 0.09094 0.08670 -0.2423 0.6597 0.0210
-11.250 0.6378 0.08908 0.08485 -0.2427 0.6588 0.0210
-11.000 0.6457 0.08735 0.08312 -0.2432 0.6579 0.0213
-10.750 0.6526 0.08555 0.08132 -0.2435 0.6568 0.0215
-10.500 0.6588 0.08371 0.07949 -0.2437 0.6558 0.0218
-10.250 0.6567 0.08076 0.07652 -0.2437 0.6546 0.0227
-10.000 0.6630 0.07912 0.07489 -0.2438 0.6533 0.0227
-9.750 0.6739 0.07816 0.07393 -0.2439 0.6518 0.0229
-9.500 0.6822 0.07679 0.07257 -0.2440 0.6509 0.0230
-9.250 0.6919 0.07559 0.07139 -0.2441 0.6504 0.0232
-9.000 0.6997 0.07421 0.07003 -0.2441 0.6498 0.0233
-8.750 0.7066 0.07279 0.06863 -0.2440 0.6491 0.0235
-8.500 0.7133 0.07140 0.06726 -0.2437 0.6484 0.0237
-8.250 0.7191 0.07000 0.06589 -0.2434 0.6476 0.0239
-3.750 0.7606 0.01633 0.01131 -0.2654 0.6270 0.0454
-3.500 0.7847 0.01519 0.01002 -0.2661 0.6258 0.0463
-3.250 0.8075 0.01443 0.00917 -0.2662 0.6246 0.0471
-3.000 0.8291 0.01387 0.00850 -0.2657 0.6232 0.0480
-2.750 0.8502 0.01344 0.00798 -0.2651 0.6218 0.0487
-2.500 0.8715 0.01326 0.00771 -0.2642 0.6205 0.0494
-2.250 0.8928 0.01315 0.00752 -0.2633 0.6189 0.0500
-2.000 0.9153 0.01307 0.00738 -0.2626 0.6174 0.0507
-1.750 0.9383 0.01303 0.00733 -0.2620 0.6166 0.0516
-1.500 0.9603 0.01304 0.00733 -0.2612 0.6158 0.0523
-1.250 0.9821 0.01305 0.00733 -0.2603 0.6148 0.0530
-1.000 1.0041 0.01308 0.00733 -0.2595 0.6138 0.0538
-0.750 1.0260 0.01310 0.00733 -0.2586 0.6126 0.0546
-0.500 1.0478 0.01314 0.00734 -0.2578 0.6112 0.0552
-0.250 1.0691 0.01318 0.00736 -0.2568 0.6097 0.0559
0.000 1.0891 0.01328 0.00746 -0.2557 0.6080 0.0566
0.250 1.1087 0.01342 0.00757 -0.2544 0.6066 0.0572
0.500 1.1284 0.01356 0.00770 -0.2532 0.6050 0.0581
0.750 1.1481 0.01371 0.00783 -0.2520 0.6035 0.0590
1.000 1.1680 0.01387 0.00795 -0.2509 0.6019 0.0597
1.250 1.1892 0.01401 0.00806 -0.2500 0.6006 0.0604
1.500 1.2093 0.01415 0.00821 -0.2489 0.5996 0.0610
1.750 1.2293 0.01431 0.00839 -0.2478 0.5984 0.0617
2.000 1.2496 0.01449 0.00860 -0.2468 0.5971 0.0626
2.250 1.2700 0.01468 0.00879 -0.2458 0.5957 0.0635
2.500 1.2900 0.01488 0.00899 -0.2447 0.5941 0.0643
2.750 1.3093 0.01510 0.00922 -0.2436 0.5924 0.0652
3.000 1.3262 0.01541 0.00952 -0.2420 0.5905 0.0658
3.250 1.3433 0.01572 0.00982 -0.2406 0.5887 0.0664
3.500 1.3605 0.01603 0.01012 -0.2391 0.5868 0.0674
3.750 1.3790 0.01632 0.01040 -0.2379 0.5849 0.0683
4.000 1.3985 0.01659 0.01070 -0.2369 0.5838 0.0694
4.250 1.4160 0.01694 0.01109 -0.2356 0.5824 0.0703
4.500 1.4340 0.01729 0.01146 -0.2343 0.5810 0.0711
4.750 1.4517 0.01766 0.01184 -0.2331 0.5791 0.0721
5.000 1.4684 0.01807 0.01226 -0.2317 0.5768 0.0729
5.250 1.4847 0.01850 0.01271 -0.2302 0.5747 0.0742
5.500 1.4969 0.01911 0.01332 -0.2282 0.5721 0.0752
5.750 1.5107 0.01966 0.01386 -0.2264 0.5693 0.0764
6.000 1.5277 0.02012 0.01436 -0.2251 0.5676 0.0773
6.250 1.5438 0.02064 0.01491 -0.2238 0.5659 0.0786
6.500 1.5582 0.02125 0.01555 -0.2222 0.5640 0.0797
6.750 1.5721 0.02188 0.01621 -0.2205 0.5612 0.0809
7.000 1.5858 0.02253 0.01688 -0.2189 0.5584 0.0831
7.250 1.5912 0.02362 0.01795 -0.2161 0.5541 0.0848
7.500 1.6026 0.02445 0.01882 -0.2142 0.5506 0.0867
7.750 1.6152 0.02525 0.01965 -0.2125 0.5476 0.0884
8.000 1.6247 0.02623 0.02067 -0.2105 0.5446 0.0920
8.250 1.6378 0.02700 0.02148 -0.2089 0.5423 0.0972
8.500 1.6501 0.02782 0.02233 -0.2073 0.5398 0.1091
8.750 1.6575 0.02893 0.02348 -0.2050 0.5368 0.1305
9.000 1.6709 0.02974 0.02438 -0.2036 0.5351 0.1543
9.250 1.6833 0.03063 0.02533 -0.2021 0.5326 0.1669
9.500 1.6920 0.03177 0.02653 -0.2002 0.5297 0.1770
9.750 1.6994 0.03300 0.02779 -0.1981 0.5260 0.1849
10.000 1.7051 0.03432 0.02910 -0.1958 0.5211 0.1929
10.250 1.7118 0.03567 0.03051 -0.1937 0.5180 0.1995
10.500 1.7195 0.03695 0.03184 -0.1918 0.5142 0.2066
10.750 1.7270 0.03822 0.03314 -0.1898 0.5098 0.2120
11.000 1.7288 0.03993 0.03484 -0.1873 0.5050 0.2161
11.250 1.7357 0.04130 0.03626 -0.1854 0.5010 0.2206
11.500 1.7421 0.04273 0.03773 -0.1834 0.4954 0.2262
11.750 1.7463 0.04432 0.03933 -0.1813 0.4910 0.2316
12.000 1.7479 0.04611 0.04114 -0.1789 0.4854 0.2352
12.250 1.7558 0.04746 0.04252 -0.1772 0.4801 0.2383
12.500 1.7523 0.04969 0.04475 -0.1743 0.4721 0.2420
12.750 1.7468 0.05217 0.04723 -0.1713 0.4596 0.2469
13.000 1.7448 0.05434 0.04938 -0.1687 0.4493 0.2509
13.250 1.7328 0.05743 0.05245 -0.1652 0.4361 0.2524
13.500 1.7123 0.06131 0.05624 -0.1609 0.4128 0.2537
13.750 1.6269 0.07136 0.06595 -0.1510 0.3537 0.2493
14.000 1.6023 0.07611 0.07061 -0.1470 0.3310 0.2509
14.250 1.5942 0.07930 0.07373 -0.1446 0.3166 0.2541
14.500 1.5903 0.08212 0.07654 -0.1426 0.3066 0.2562
14.750 1.5901 0.08460 0.07900 -0.1409 0.2974 0.2596
15.000 1.5938 0.08666 0.08106 -0.1396 0.2891 0.2640
15.250 1.5935 0.08919 0.08359 -0.1381 0.2811 0.2676
15.500 1.5975 0.09129 0.08569 -0.1369 0.2729 0.2711
15.750 1.5989 0.09365 0.08802 -0.1355 0.2638 0.2745
16.000 1.6045 0.09554 0.08991 -0.1345 0.2544 0.2784
16.250 1.6033 0.09823 0.09258 -0.1332 0.2447 0.2832
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