GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 507 AIRFOIL (goe507-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.05 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe507-il-1000000.txt Download as CSV file: xf-goe507-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -1.0521 0.03658 0.03401 -0.0742 1.0000 0.0116
-13.500 -1.0665 0.03184 0.02898 -0.0738 1.0000 0.0117
-13.250 -1.0719 0.02845 0.02535 -0.0722 1.0000 0.0120
-13.000 -1.0657 0.02635 0.02308 -0.0707 1.0000 0.0123
-12.750 -1.0538 0.02490 0.02152 -0.0692 1.0000 0.0127
-12.500 -1.0404 0.02362 0.02011 -0.0678 1.0000 0.0130
-12.250 -1.0259 0.02248 0.01886 -0.0663 1.0000 0.0133
-12.000 -1.0100 0.02156 0.01783 -0.0648 1.0000 0.0137
-11.750 -0.9945 0.02066 0.01681 -0.0631 1.0000 0.0141
-11.500 -0.9791 0.01989 0.01592 -0.0613 1.0000 0.0144
-11.250 -0.9669 0.01896 0.01486 -0.0589 1.0000 0.0148
-11.000 -0.9475 0.01771 0.01349 -0.0583 0.9991 0.0156
-10.750 -0.9168 0.01686 0.01255 -0.0595 0.9973 0.0163
-10.500 -0.8854 0.01615 0.01175 -0.0608 0.9954 0.0171
-10.250 -0.8538 0.01551 0.01099 -0.0620 0.9935 0.0178
-10.000 -0.8247 0.01465 0.01002 -0.0628 0.9906 0.0189
-9.750 -0.7937 0.01401 0.00934 -0.0638 0.9880 0.0201
-9.500 -0.7613 0.01357 0.00884 -0.0650 0.9860 0.0214
-9.250 -0.7286 0.01305 0.00823 -0.0663 0.9844 0.0227
-9.000 -0.6950 0.01262 0.00781 -0.0677 0.9831 0.0247
-8.750 -0.6648 0.01237 0.00751 -0.0683 0.9791 0.0263
-8.500 -0.6332 0.01198 0.00709 -0.0692 0.9756 0.0281
-8.250 -0.5996 0.01192 0.00706 -0.0704 0.9729 0.0300
-8.000 -0.5651 0.01195 0.00708 -0.0718 0.9705 0.0317
-7.750 -0.5357 0.01196 0.00705 -0.0720 0.9646 0.0327
-7.500 -0.5061 0.01160 0.00668 -0.0725 0.9592 0.0347
-7.250 -0.4755 0.01165 0.00673 -0.0729 0.9540 0.0359
-7.000 -0.4478 0.01169 0.00675 -0.0728 0.9468 0.0372
-6.750 -0.4190 0.01173 0.00674 -0.0728 0.9410 0.0385
-6.500 -0.3921 0.01178 0.00675 -0.0725 0.9340 0.0392
-6.250 -0.3674 0.01110 0.00596 -0.0719 0.9268 0.0408
-6.000 -0.3416 0.01090 0.00576 -0.0714 0.9191 0.0420
-5.750 -0.3150 0.01084 0.00567 -0.0710 0.9117 0.0432
-5.500 -0.2885 0.01072 0.00551 -0.0707 0.9047 0.0444
-5.250 -0.2619 0.01059 0.00534 -0.0703 0.8977 0.0456
-5.000 -0.2353 0.01043 0.00512 -0.0699 0.8913 0.0466
-4.750 -0.2083 0.01037 0.00502 -0.0696 0.8844 0.0475
-4.500 -0.1812 0.01032 0.00491 -0.0693 0.8782 0.0479
-4.250 -0.1571 0.00944 0.00397 -0.0686 0.8710 0.0498
-4.000 -0.1313 0.00908 0.00357 -0.0681 0.8646 0.0509
-3.750 -0.1048 0.00882 0.00329 -0.0677 0.8586 0.0519
-3.500 -0.0781 0.00862 0.00308 -0.0674 0.8524 0.0530
-3.250 -0.0513 0.00844 0.00286 -0.0670 0.8468 0.0540
-3.000 -0.0244 0.00824 0.00264 -0.0667 0.8406 0.0550
-2.750 0.0024 0.00807 0.00243 -0.0663 0.8346 0.0560
-2.500 0.0294 0.00792 0.00226 -0.0660 0.8287 0.0569
-2.250 0.0565 0.00778 0.00210 -0.0657 0.8222 0.0576
-2.000 0.0836 0.00769 0.00197 -0.0654 0.8163 0.0583
-1.750 0.1110 0.00758 0.00187 -0.0652 0.8096 0.0587
-1.500 0.1376 0.00738 0.00161 -0.0648 0.8030 0.0601
-1.250 0.1646 0.00723 0.00144 -0.0644 0.7960 0.0621
-1.000 0.1916 0.00711 0.00131 -0.0641 0.7885 0.0645
-0.750 0.2186 0.00702 0.00122 -0.0637 0.7787 0.0668
-0.500 0.2453 0.00696 0.00112 -0.0633 0.7673 0.0693
-0.250 0.2722 0.00692 0.00105 -0.0630 0.7563 0.0725
0.000 0.2980 0.00667 0.00098 -0.0625 0.7437 0.1290
0.250 0.3239 0.00652 0.00099 -0.0620 0.7296 0.1899
0.500 0.3506 0.00647 0.00098 -0.0617 0.7177 0.2147
0.750 0.3771 0.00641 0.00097 -0.0613 0.7038 0.2411
1.000 0.4025 0.00627 0.00098 -0.0607 0.6864 0.3057
1.250 0.4244 0.00585 0.00101 -0.0597 0.6617 0.5006
1.750 0.4868 0.00507 0.00125 -0.0609 0.5821 0.9726
2.000 0.5320 0.00537 0.00136 -0.0647 0.5414 0.9888
2.250 0.5807 0.00562 0.00147 -0.0694 0.5095 0.9978
2.500 0.6156 0.00582 0.00154 -0.0710 0.4825 1.0000
2.750 0.6382 0.00602 0.00163 -0.0699 0.4533 1.0000
3.000 0.6607 0.00623 0.00172 -0.0687 0.4236 1.0000
3.250 0.6826 0.00650 0.00184 -0.0675 0.3886 1.0000
3.500 0.7043 0.00679 0.00197 -0.0663 0.3503 1.0000
3.750 0.7250 0.00717 0.00215 -0.0649 0.3052 1.0000
4.000 0.7441 0.00768 0.00238 -0.0632 0.2472 1.0000
4.250 0.7634 0.00821 0.00264 -0.0616 0.1947 1.0000
4.500 0.7775 0.00919 0.00310 -0.0592 0.0911 1.0000
4.750 0.7986 0.00961 0.00341 -0.0579 0.0705 1.0000
5.000 0.8218 0.00984 0.00363 -0.0570 0.0665 1.0000
5.250 0.8445 0.01013 0.00389 -0.0559 0.0618 1.0000
5.500 0.8675 0.01039 0.00416 -0.0549 0.0582 1.0000
5.750 0.8912 0.01059 0.00437 -0.0541 0.0564 1.0000
6.000 0.9146 0.01082 0.00461 -0.0532 0.0540 1.0000
6.250 0.9372 0.01112 0.00490 -0.0521 0.0509 1.0000
6.500 0.9592 0.01148 0.00527 -0.0510 0.0474 1.0000
6.750 0.9834 0.01164 0.00544 -0.0503 0.0457 1.0000
7.000 1.0069 0.01185 0.00566 -0.0495 0.0430 1.0000
7.250 1.0285 0.01226 0.00603 -0.0484 0.0387 1.0000
7.500 1.0526 0.01242 0.00622 -0.0477 0.0367 1.0000
7.750 1.0755 0.01269 0.00646 -0.0468 0.0336 1.0000
8.000 1.0972 0.01307 0.00683 -0.0457 0.0305 1.0000
8.250 1.1198 0.01337 0.00713 -0.0448 0.0283 1.0000
8.500 1.1398 0.01387 0.00761 -0.0435 0.0252 1.0000
8.750 1.1620 0.01418 0.00795 -0.0426 0.0240 1.0000
9.000 1.1832 0.01455 0.00834 -0.0415 0.0226 1.0000
9.250 1.2021 0.01510 0.00889 -0.0400 0.0209 1.0000
9.500 1.2209 0.01563 0.00947 -0.0385 0.0198 1.0000
9.750 1.2408 0.01605 0.00994 -0.0373 0.0190 1.0000
10.000 1.2600 0.01650 0.01042 -0.0359 0.0181 1.0000
10.250 1.2774 0.01706 0.01099 -0.0343 0.0170 1.0000
10.500 1.2893 0.01794 0.01193 -0.0318 0.0161 1.0000
10.750 1.3062 0.01836 0.01241 -0.0301 0.0157 1.0000
11.000 1.3204 0.01887 0.01298 -0.0279 0.0151 1.0000
11.250 1.3337 0.01943 0.01359 -0.0256 0.0147 1.0000
11.500 1.3465 0.02003 0.01424 -0.0234 0.0142 1.0000
11.750 1.3583 0.02073 0.01498 -0.0212 0.0138 1.0000
12.000 1.3664 0.02167 0.01598 -0.0186 0.0133 1.0000
12.250 1.3664 0.02319 0.01760 -0.0152 0.0128 1.0000
12.500 1.3791 0.02392 0.01841 -0.0135 0.0125 1.0000
12.750 1.3897 0.02482 0.01938 -0.0117 0.0123 1.0000
13.000 1.4024 0.02560 0.02023 -0.0102 0.0119 1.0000
13.250 1.4087 0.02688 0.02160 -0.0082 0.0118 1.0000
13.500 1.4186 0.02792 0.02271 -0.0067 0.0114 1.0000
13.750 1.4282 0.02902 0.02387 -0.0053 0.0111 1.0000
14.000 1.4332 0.03054 0.02547 -0.0037 0.0109 1.0000
14.250 1.4379 0.03215 0.02716 -0.0024 0.0106 1.0000
14.500 1.4397 0.03409 0.02916 -0.0010 0.0104 1.0000
14.750 1.4346 0.03676 0.03195 0.0003 0.0101 1.0000
15.000 1.4223 0.04034 0.03569 0.0015 0.0099 1.0000
15.250 1.4271 0.04234 0.03778 0.0019 0.0098 1.0000
15.500 1.4246 0.04518 0.04075 0.0022 0.0097 1.0000
15.750 1.4261 0.04773 0.04340 0.0022 0.0096 1.0000
16.000 1.4206 0.05122 0.04702 0.0020 0.0096 1.0000
16.250 1.4170 0.05468 0.05061 0.0013 0.0095 1.0000
16.500 1.4150 0.05814 0.05418 0.0004 0.0093 1.0000
16.750 1.4092 0.06226 0.05842 -0.0009 0.0092 1.0000
17.000 1.3997 0.06707 0.06336 -0.0026 0.0091 1.0000
17.250 1.3905 0.07204 0.06846 -0.0046 0.0090 1.0000
17.500 1.3794 0.07748 0.07402 -0.0069 0.0090 1.0000
17.750 1.3636 0.08380 0.08048 -0.0097 0.0090 1.0000
18.000 1.3498 0.09007 0.08688 -0.0128 0.0089 1.0000
18.250 1.3334 0.09695 0.09389 -0.0162 0.0089 1.0000
18.500 1.3189 0.10375 0.10081 -0.0198 0.0088 1.0000
18.750 1.2999 0.11161 0.10880 -0.0240 0.0088 1.0000
19.000 1.2779 0.12027 0.11762 -0.0288 0.0088 1.0000
19.250 1.2592 0.12855 0.12602 -0.0335 0.0088 1.0000
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Polar data table (+)
Polar graphs
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