GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 623 AIRFOIL (goe623-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.37 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe623-il-1000000-n5.txt Download as CSV file: xf-goe623-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 623 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
------ -------- --------- --------- -------- -------- --------
-15.250 -1.1036 0.03693 0.03401 -0.0843 1.0000 0.0076
-15.000 -1.1192 0.03323 0.03013 -0.0847 1.0000 0.0076
-14.750 -1.1193 0.03096 0.02770 -0.0838 1.0000 0.0077
-14.500 -1.1125 0.02914 0.02574 -0.0829 1.0000 0.0078
-14.250 -1.1037 0.02750 0.02396 -0.0818 1.0000 0.0079
-14.000 -1.0937 0.02597 0.02232 -0.0805 1.0000 0.0081
-13.750 -1.0819 0.02471 0.02095 -0.0791 1.0000 0.0084
-13.500 -1.0688 0.02362 0.01978 -0.0775 1.0000 0.0086
-13.250 -1.0501 0.02260 0.01866 -0.0769 0.9991 0.0089
-13.000 -1.0232 0.02156 0.01753 -0.0779 0.9965 0.0092
-12.500 -0.9683 0.01976 0.01552 -0.0796 0.9903 0.0099
-12.250 -0.9398 0.01897 0.01463 -0.0805 0.9859 0.0102
-12.000 -0.9117 0.01818 0.01376 -0.0812 0.9789 0.0107
-11.750 -0.8821 0.01752 0.01304 -0.0821 0.9693 0.0113
-11.500 -0.8536 0.01694 0.01240 -0.0826 0.9559 0.0119
-11.250 -0.8275 0.01642 0.01178 -0.0826 0.9406 0.0124
-11.000 -0.8030 0.01594 0.01117 -0.0821 0.9248 0.0129
-10.750 -0.7787 0.01549 0.01062 -0.0816 0.9102 0.0134
-10.500 -0.7535 0.01515 0.01021 -0.0812 0.8984 0.0140
-10.250 -0.7276 0.01485 0.00985 -0.0809 0.8889 0.0146
-10.000 -0.7015 0.01454 0.00948 -0.0807 0.8809 0.0153
-9.750 -0.6752 0.01423 0.00909 -0.0805 0.8731 0.0159
-9.500 -0.6488 0.01393 0.00869 -0.0803 0.8664 0.0164
-9.250 -0.6224 0.01359 0.00831 -0.0801 0.8592 0.0171
-9.000 -0.5954 0.01337 0.00805 -0.0799 0.8525 0.0177
-8.750 -0.5681 0.01314 0.00778 -0.0799 0.8460 0.0182
-8.500 -0.5410 0.01292 0.00750 -0.0797 0.8398 0.0188
-8.250 -0.5136 0.01270 0.00722 -0.0797 0.8341 0.0194
-8.000 -0.4862 0.01248 0.00694 -0.0796 0.8274 0.0200
-7.750 -0.4587 0.01228 0.00667 -0.0795 0.8210 0.0205
-7.500 -0.4310 0.01207 0.00640 -0.0794 0.8147 0.0207
-7.250 -0.4046 0.01160 0.00588 -0.0793 0.8083 0.0215
-7.000 -0.3771 0.01135 0.00559 -0.0792 0.8024 0.0221
-6.750 -0.3493 0.01113 0.00533 -0.0792 0.7954 0.0227
-6.500 -0.3217 0.01092 0.00507 -0.0791 0.7883 0.0233
-6.250 -0.2939 0.01071 0.00481 -0.0791 0.7802 0.0239
-6.000 -0.2662 0.01050 0.00454 -0.0790 0.7721 0.0245
-5.750 -0.2383 0.01029 0.00427 -0.0790 0.7634 0.0250
-5.500 -0.2103 0.01013 0.00405 -0.0790 0.7545 0.0254
-5.250 -0.1824 0.00996 0.00382 -0.0789 0.7438 0.0257
-5.000 -0.1545 0.00980 0.00360 -0.0789 0.7317 0.0259
-4.750 -0.1272 0.00951 0.00322 -0.0787 0.7174 0.0267
-4.500 -0.0996 0.00932 0.00295 -0.0786 0.7014 0.0276
-4.250 -0.0719 0.00919 0.00274 -0.0786 0.6856 0.0283
-4.000 -0.0441 0.00908 0.00256 -0.0785 0.6706 0.0288
-3.750 -0.0161 0.00898 0.00239 -0.0785 0.6568 0.0294
-3.500 0.0119 0.00890 0.00225 -0.0784 0.6440 0.0301
-3.250 0.0399 0.00883 0.00211 -0.0784 0.6323 0.0308
-3.000 0.0681 0.00876 0.00199 -0.0784 0.6217 0.0315
-2.750 0.0964 0.00870 0.00189 -0.0785 0.6135 0.0321
-2.500 0.1247 0.00863 0.00178 -0.0785 0.6049 0.0339
-2.250 0.1531 0.00855 0.00169 -0.0786 0.5974 0.0369
-2.000 0.1814 0.00848 0.00161 -0.0786 0.5897 0.0420
-1.750 0.2093 0.00832 0.00152 -0.0787 0.5816 0.0701
-1.500 0.2372 0.00825 0.00146 -0.0787 0.5707 0.0882
-1.250 0.2652 0.00814 0.00144 -0.0787 0.5599 0.1232
-1.000 0.2935 0.00813 0.00143 -0.0788 0.5509 0.1361
-0.750 0.3217 0.00813 0.00141 -0.0788 0.5403 0.1447
-0.500 0.3499 0.00815 0.00140 -0.0789 0.5281 0.1506
-0.250 0.3781 0.00816 0.00139 -0.0790 0.5168 0.1593
0.000 0.4062 0.00818 0.00139 -0.0790 0.5078 0.1685
0.250 0.4347 0.00815 0.00139 -0.0791 0.5016 0.1804
0.500 0.4629 0.00808 0.00140 -0.0792 0.4950 0.2107
0.750 0.4908 0.00798 0.00143 -0.0793 0.4888 0.2636
1.000 0.5188 0.00788 0.00146 -0.0794 0.4804 0.3195
1.250 0.5463 0.00773 0.00150 -0.0795 0.4714 0.4004
1.500 0.5733 0.00751 0.00156 -0.0795 0.4614 0.5144
1.750 0.5999 0.00722 0.00163 -0.0795 0.4521 0.6514
2.000 0.6258 0.00703 0.00172 -0.0791 0.4414 0.7559
2.250 0.6508 0.00694 0.00181 -0.0785 0.4284 0.8363
2.500 0.6736 0.00691 0.00192 -0.0772 0.4124 0.9106
2.750 0.7009 0.00705 0.00203 -0.0770 0.3885 0.9622
3.000 0.7347 0.00734 0.00217 -0.0784 0.3577 0.9877
3.250 0.7673 0.00762 0.00232 -0.0797 0.3326 1.0000
3.500 0.7928 0.00786 0.00246 -0.0793 0.3140 1.0000
3.750 0.8185 0.00809 0.00261 -0.0790 0.2977 1.0000
4.000 0.8443 0.00831 0.00276 -0.0787 0.2831 1.0000
4.250 0.8703 0.00853 0.00291 -0.0784 0.2696 1.0000
4.500 0.8962 0.00876 0.00307 -0.0782 0.2573 1.0000
4.750 0.9221 0.00899 0.00325 -0.0779 0.2455 1.0000
5.000 0.9479 0.00922 0.00342 -0.0776 0.2340 1.0000
5.250 0.9739 0.00943 0.00360 -0.0774 0.2241 1.0000
5.500 0.9996 0.00967 0.00379 -0.0771 0.2153 1.0000
5.750 1.0257 0.00987 0.00397 -0.0769 0.2084 1.0000
6.000 1.0513 0.01010 0.00417 -0.0766 0.2015 1.0000
6.250 1.0771 0.01032 0.00438 -0.0764 0.1942 1.0000
6.500 1.1022 0.01058 0.00460 -0.0760 0.1870 1.0000
6.750 1.1276 0.01082 0.00482 -0.0758 0.1798 1.0000
7.000 1.1523 0.01111 0.00507 -0.0754 0.1716 1.0000
7.250 1.1773 0.01136 0.00531 -0.0750 0.1651 1.0000
7.500 1.2016 0.01166 0.00558 -0.0746 0.1583 1.0000
7.750 1.2265 0.01189 0.00582 -0.0742 0.1531 1.0000
8.000 1.2501 0.01223 0.00612 -0.0737 0.1453 1.0000
8.250 1.2743 0.01250 0.00639 -0.0732 0.1389 1.0000
8.500 1.2968 0.01288 0.00672 -0.0726 0.1289 1.0000
8.750 1.3181 0.01334 0.00710 -0.0717 0.1146 1.0000
9.000 1.3271 0.01464 0.00807 -0.0690 0.0652 1.0000
9.250 1.3427 0.01542 0.00877 -0.0673 0.0488 1.0000
9.500 1.3602 0.01602 0.00934 -0.0658 0.0405 1.0000
9.750 1.3761 0.01664 0.00993 -0.0641 0.0322 1.0000
10.000 1.3884 0.01737 0.01060 -0.0618 0.0227 1.0000
10.250 1.4015 0.01808 0.01129 -0.0597 0.0171 1.0000
10.500 1.4162 0.01872 0.01195 -0.0580 0.0149 1.0000
10.750 1.4310 0.01938 0.01263 -0.0564 0.0133 1.0000
11.000 1.4460 0.02004 0.01333 -0.0549 0.0124 1.0000
11.250 1.4597 0.02080 0.01412 -0.0533 0.0114 1.0000
11.500 1.4725 0.02165 0.01501 -0.0517 0.0105 1.0000
11.750 1.4865 0.02244 0.01586 -0.0503 0.0101 1.0000
12.000 1.4995 0.02333 0.01679 -0.0489 0.0095 1.0000
12.250 1.5114 0.02433 0.01784 -0.0476 0.0090 1.0000
12.500 1.5221 0.02544 0.01899 -0.0462 0.0085 1.0000
12.750 1.5315 0.02671 0.02031 -0.0448 0.0080 1.0000
13.000 1.5420 0.02791 0.02158 -0.0436 0.0078 1.0000
13.250 1.5518 0.02921 0.02295 -0.0425 0.0076 1.0000
13.500 1.5607 0.03063 0.02443 -0.0414 0.0073 1.0000
13.750 1.5684 0.03218 0.02604 -0.0404 0.0070 1.0000
14.000 1.5751 0.03387 0.02780 -0.0394 0.0068 1.0000
14.250 1.5806 0.03572 0.02972 -0.0386 0.0066 1.0000
14.500 1.5846 0.03777 0.03184 -0.0377 0.0064 1.0000
14.750 1.5868 0.04007 0.03421 -0.0370 0.0062 1.0000
15.000 1.5869 0.04266 0.03690 -0.0364 0.0060 1.0000
15.250 1.5891 0.04513 0.03945 -0.0360 0.0059 1.0000
15.500 1.5906 0.04774 0.04214 -0.0358 0.0057 1.0000
15.750 1.5908 0.05059 0.04508 -0.0357 0.0056 1.0000
16.000 1.5899 0.05366 0.04825 -0.0357 0.0055 1.0000
16.250 1.5883 0.05689 0.05156 -0.0359 0.0054 1.0000
16.500 1.5851 0.06034 0.05511 -0.0362 0.0053 1.0000
16.750 1.5804 0.06409 0.05896 -0.0366 0.0052 1.0000
17.000 1.5744 0.06810 0.06307 -0.0373 0.0051 1.0000
17.250 1.5671 0.07234 0.06740 -0.0380 0.0050 1.0000
17.500 1.5583 0.07683 0.07200 -0.0389 0.0049 1.0000
17.750 1.5481 0.08165 0.07692 -0.0400 0.0049 1.0000
18.000 1.5365 0.08681 0.08219 -0.0413 0.0048 1.0000
18.250 1.5239 0.09217 0.08767 -0.0428 0.0047 1.0000
18.500 1.5098 0.09788 0.09349 -0.0446 0.0047 1.0000
18.750 1.4946 0.10390 0.09963 -0.0466 0.0047 1.0000
19.000 1.4792 0.11007 0.10591 -0.0487 0.0046 1.0000
19.250 1.4627 0.11647 0.11243 -0.0511 0.0046 1.0000
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