GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 507 AIRFOIL (goe507-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.16 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe507-il-1000000-n5.txt Download as CSV file: xf-goe507-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 507 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6451 0.11336 0.11138 -0.0221 1.0000 0.0073
-13.750 -0.6711 0.10393 0.10192 -0.0269 1.0000 0.0074
-13.250 -1.0344 0.03277 0.02991 -0.0734 1.0000 0.0056
-13.000 -1.0337 0.02952 0.02645 -0.0724 1.0000 0.0058
-12.750 -1.0271 0.02724 0.02399 -0.0710 1.0000 0.0059
-12.500 -1.0163 0.02555 0.02215 -0.0696 1.0000 0.0060
-12.250 -1.0047 0.02403 0.02048 -0.0681 1.0000 0.0061
-12.000 -0.9853 0.02270 0.01901 -0.0678 0.9989 0.0064
-11.750 -0.9596 0.02135 0.01749 -0.0687 0.9951 0.0066
-11.500 -0.9341 0.02023 0.01622 -0.0693 0.9907 0.0067
-11.250 -0.9068 0.01914 0.01500 -0.0701 0.9870 0.0069
-11.000 -0.8799 0.01797 0.01369 -0.0709 0.9833 0.0073
-10.750 -0.8514 0.01705 0.01267 -0.0718 0.9794 0.0076
-10.500 -0.8215 0.01623 0.01174 -0.0729 0.9759 0.0080
-10.250 -0.7927 0.01552 0.01093 -0.0736 0.9704 0.0084
-9.750 -0.7343 0.01420 0.00940 -0.0750 0.9591 0.0094
-9.500 -0.7063 0.01359 0.00870 -0.0754 0.9526 0.0101
-9.250 -0.6794 0.01308 0.00811 -0.0754 0.9450 0.0108
-9.000 -0.6531 0.01266 0.00760 -0.0753 0.9373 0.0113
-8.500 -0.6024 0.01172 0.00651 -0.0745 0.9221 0.0135
-8.000 -0.5515 0.01093 0.00559 -0.0737 0.9090 0.0167
-7.750 -0.5260 0.01057 0.00518 -0.0733 0.9024 0.0190
-7.500 -0.5003 0.01022 0.00479 -0.0729 0.8963 0.0225
-7.250 -0.4742 0.00996 0.00456 -0.0726 0.8901 0.0275
-7.000 -0.4472 0.00986 0.00449 -0.0724 0.8848 0.0328
-6.750 -0.4196 0.00981 0.00446 -0.0722 0.8796 0.0364
-6.500 -0.3923 0.00975 0.00435 -0.0720 0.8740 0.0383
-6.250 -0.3651 0.00970 0.00426 -0.0718 0.8680 0.0395
-6.000 -0.3377 0.00967 0.00419 -0.0716 0.8606 0.0401
-5.750 -0.3104 0.00967 0.00413 -0.0714 0.8535 0.0405
-5.500 -0.2843 0.00934 0.00375 -0.0710 0.8466 0.0417
-5.250 -0.2580 0.00912 0.00347 -0.0706 0.8400 0.0433
-5.000 -0.2308 0.00900 0.00333 -0.0704 0.8336 0.0447
-4.750 -0.2036 0.00892 0.00323 -0.0702 0.8268 0.0460
-4.500 -0.1765 0.00879 0.00306 -0.0700 0.8205 0.0469
-4.250 -0.1498 0.00860 0.00282 -0.0696 0.8129 0.0473
-4.000 -0.1230 0.00844 0.00259 -0.0693 0.8061 0.0477
-3.750 -0.0960 0.00827 0.00239 -0.0691 0.7993 0.0482
-3.500 -0.0690 0.00813 0.00220 -0.0688 0.7933 0.0488
-3.250 -0.0417 0.00800 0.00205 -0.0686 0.7874 0.0497
-3.000 -0.0145 0.00789 0.00190 -0.0683 0.7808 0.0505
-2.750 0.0127 0.00779 0.00176 -0.0681 0.7747 0.0512
-2.500 0.0401 0.00769 0.00164 -0.0679 0.7678 0.0518
-2.250 0.0672 0.00762 0.00154 -0.0676 0.7610 0.0524
-2.000 0.0947 0.00755 0.00146 -0.0675 0.7538 0.0528
-1.500 0.1493 0.00743 0.00129 -0.0670 0.7382 0.0535
-1.250 0.1763 0.00735 0.00117 -0.0667 0.7295 0.0548
-1.000 0.2035 0.00728 0.00108 -0.0665 0.7193 0.0559
-0.750 0.2303 0.00725 0.00101 -0.0662 0.7049 0.0570
-0.500 0.2563 0.00727 0.00095 -0.0657 0.6817 0.0581
-0.250 0.2812 0.00737 0.00091 -0.0650 0.6396 0.0591
0.000 0.3054 0.00755 0.00090 -0.0641 0.5882 0.0603
0.250 0.3304 0.00769 0.00091 -0.0635 0.5511 0.0617
0.500 0.3563 0.00779 0.00093 -0.0631 0.5274 0.0633
0.750 0.3824 0.00789 0.00096 -0.0627 0.5046 0.0655
1.000 0.4080 0.00797 0.00099 -0.0622 0.4805 0.0765
1.250 0.4333 0.00784 0.00104 -0.0618 0.4639 0.1600
1.500 0.4594 0.00789 0.00110 -0.0614 0.4450 0.1827
1.750 0.4852 0.00798 0.00117 -0.0610 0.4223 0.2019
2.000 0.5109 0.00806 0.00125 -0.0606 0.4003 0.2238
2.250 0.5363 0.00813 0.00133 -0.0601 0.3769 0.2588
2.500 0.5586 0.00784 0.00146 -0.0593 0.3533 0.4572
2.750 0.5682 0.00680 0.00164 -0.0554 0.3307 0.9029
3.000 0.6281 0.00723 0.00190 -0.0628 0.2727 0.9825
3.250 0.6643 0.00756 0.00208 -0.0648 0.2402 0.9937
3.500 0.6985 0.00785 0.00224 -0.0664 0.2138 0.9991
3.750 0.7249 0.00813 0.00241 -0.0662 0.1902 1.0000
4.000 0.7459 0.00852 0.00263 -0.0649 0.1516 1.0000
4.250 0.7630 0.00926 0.00302 -0.0630 0.0796 1.0000
4.500 0.7858 0.00953 0.00323 -0.0620 0.0687 1.0000
4.750 0.8092 0.00976 0.00343 -0.0611 0.0641 1.0000
5.000 0.8326 0.00998 0.00364 -0.0602 0.0593 1.0000
5.250 0.8565 0.01016 0.00382 -0.0594 0.0568 1.0000
5.500 0.8801 0.01037 0.00403 -0.0586 0.0543 1.0000
5.750 0.9036 0.01060 0.00425 -0.0577 0.0515 1.0000
6.000 0.9268 0.01085 0.00449 -0.0568 0.0484 1.0000
6.250 0.9506 0.01105 0.00471 -0.0561 0.0471 1.0000
6.500 0.9747 0.01123 0.00492 -0.0554 0.0460 1.0000
6.750 0.9984 0.01144 0.00514 -0.0546 0.0435 1.0000
7.000 1.0214 0.01172 0.00539 -0.0537 0.0365 1.0000
7.250 1.0437 0.01206 0.00567 -0.0528 0.0288 1.0000
7.500 1.0656 0.01243 0.00599 -0.0518 0.0230 1.0000
7.750 1.0871 0.01283 0.00636 -0.0507 0.0191 1.0000
8.000 1.1091 0.01318 0.00673 -0.0497 0.0169 1.0000
8.250 1.1301 0.01360 0.00715 -0.0486 0.0148 1.0000
8.500 1.1519 0.01395 0.00752 -0.0476 0.0135 1.0000
8.750 1.1727 0.01437 0.00794 -0.0465 0.0122 1.0000
9.000 1.1932 0.01479 0.00839 -0.0453 0.0113 1.0000
9.250 1.2138 0.01519 0.00883 -0.0441 0.0104 1.0000
9.500 1.2337 0.01564 0.00930 -0.0429 0.0098 1.0000
9.750 1.2522 0.01616 0.00984 -0.0415 0.0090 1.0000
10.000 1.2715 0.01660 0.01033 -0.0401 0.0087 1.0000
10.250 1.2898 0.01708 0.01085 -0.0387 0.0083 1.0000
10.500 1.3073 0.01757 0.01140 -0.0371 0.0079 1.0000
10.750 1.3223 0.01810 0.01197 -0.0351 0.0075 1.0000
11.000 1.3354 0.01869 0.01259 -0.0328 0.0071 1.0000
11.250 1.3488 0.01926 0.01321 -0.0306 0.0068 1.0000
11.500 1.3618 0.01987 0.01388 -0.0284 0.0066 1.0000
11.750 1.3750 0.02049 0.01456 -0.0264 0.0063 1.0000
12.000 1.3873 0.02118 0.01531 -0.0243 0.0061 1.0000
12.250 1.3992 0.02192 0.01611 -0.0223 0.0059 1.0000
12.500 1.4102 0.02274 0.01700 -0.0203 0.0057 1.0000
12.750 1.4203 0.02364 0.01796 -0.0184 0.0055 1.0000
13.000 1.4280 0.02475 0.01914 -0.0163 0.0054 1.0000
13.250 1.4357 0.02589 0.02036 -0.0143 0.0052 1.0000
13.500 1.4447 0.02698 0.02153 -0.0127 0.0051 1.0000
13.750 1.4519 0.02823 0.02287 -0.0110 0.0051 1.0000
14.000 1.4590 0.02955 0.02428 -0.0094 0.0049 1.0000
14.250 1.4646 0.03104 0.02585 -0.0080 0.0048 1.0000
14.500 1.4705 0.03255 0.02745 -0.0067 0.0047 1.0000
14.750 1.4739 0.03436 0.02935 -0.0054 0.0046 1.0000
15.000 1.4782 0.03615 0.03123 -0.0044 0.0045 1.0000
15.250 1.4821 0.03806 0.03322 -0.0036 0.0044 1.0000
15.500 1.4820 0.04044 0.03571 -0.0029 0.0043 1.0000
15.750 1.4836 0.04276 0.03812 -0.0024 0.0042 1.0000
16.000 1.4814 0.04559 0.04106 -0.0021 0.0042 1.0000
16.250 1.4763 0.04892 0.04450 -0.0022 0.0041 1.0000
16.500 1.4743 0.05204 0.04773 -0.0026 0.0040 1.0000
16.750 1.4639 0.05650 0.05232 -0.0036 0.0039 1.0000
17.000 1.4543 0.06110 0.05704 -0.0050 0.0039 1.0000
17.250 1.4424 0.06628 0.06235 -0.0068 0.0039 1.0000
17.500 1.4314 0.07154 0.06774 -0.0089 0.0038 1.0000
17.750 1.4177 0.07741 0.07374 -0.0114 0.0038 1.0000
18.000 1.4021 0.08380 0.08027 -0.0143 0.0038 1.0000
18.250 1.3861 0.09046 0.08706 -0.0175 0.0038 1.0000
18.500 1.3622 0.09883 0.09558 -0.0217 0.0038 1.0000
18.750 1.3421 0.10677 0.10366 -0.0258 0.0038 1.0000
19.000 1.3231 0.11476 0.11178 -0.0300 0.0038 1.0000
19.250 1.2968 0.12443 0.12159 -0.0354 0.0038 1.0000
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Polar data table (+)
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