GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.26 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe693-il-1000000-n5.txt Download as CSV file: xf-goe693-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 693 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7208 0.12992 0.12797 -0.0247 1.0000 0.0143
-16.250 -0.7944 0.11134 0.10925 -0.0347 1.0000 0.0146
-16.000 -1.2087 0.03474 0.03154 -0.0922 1.0000 0.0107
-15.750 -1.2203 0.03204 0.02868 -0.0907 1.0000 0.0109
-15.500 -1.2203 0.03009 0.02659 -0.0892 1.0000 0.0112
-15.250 -1.2142 0.02848 0.02486 -0.0878 1.0000 0.0115
-15.000 -1.2060 0.02714 0.02341 -0.0862 1.0000 0.0118
-14.750 -1.1980 0.02600 0.02217 -0.0841 1.0000 0.0121
-14.500 -1.1806 0.02471 0.02079 -0.0838 0.9984 0.0128
-14.250 -1.1574 0.02356 0.01956 -0.0844 0.9963 0.0135
-14.000 -1.1323 0.02257 0.01848 -0.0851 0.9948 0.0143
-13.750 -1.1071 0.02169 0.01751 -0.0857 0.9927 0.0149
-13.500 -1.0827 0.02087 0.01661 -0.0859 0.9898 0.0156
-13.250 -1.0568 0.02014 0.01584 -0.0864 0.9872 0.0164
-13.000 -1.0296 0.01950 0.01514 -0.0869 0.9849 0.0171
-12.750 -1.0036 0.01891 0.01448 -0.0872 0.9820 0.0179
-12.500 -0.9785 0.01836 0.01385 -0.0871 0.9781 0.0184
-12.250 -0.9522 0.01784 0.01325 -0.0873 0.9747 0.0188
-12.000 -0.9268 0.01726 0.01262 -0.0873 0.9714 0.0196
-11.750 -0.9021 0.01682 0.01216 -0.0870 0.9667 0.0203
-11.500 -0.8768 0.01642 0.01171 -0.0868 0.9623 0.0209
-11.250 -0.8514 0.01603 0.01126 -0.0865 0.9584 0.0216
-11.000 -0.8265 0.01564 0.01080 -0.0861 0.9533 0.0221
-10.750 -0.8014 0.01528 0.01036 -0.0858 0.9481 0.0225
-10.500 -0.7758 0.01495 0.00996 -0.0854 0.9433 0.0229
-10.250 -0.7505 0.01455 0.00950 -0.0851 0.9376 0.0234
-10.000 -0.7258 0.01407 0.00896 -0.0847 0.9314 0.0241
-9.750 -0.7001 0.01369 0.00854 -0.0844 0.9251 0.0247
-9.500 -0.6742 0.01337 0.00817 -0.0841 0.9173 0.0253
-9.250 -0.6480 0.01308 0.00782 -0.0838 0.9097 0.0259
-9.000 -0.6217 0.01279 0.00747 -0.0836 0.9006 0.0265
-8.750 -0.5952 0.01252 0.00712 -0.0833 0.8905 0.0270
-8.500 -0.5686 0.01227 0.00679 -0.0831 0.8790 0.0275
-8.250 -0.5420 0.01204 0.00647 -0.0828 0.8659 0.0279
-8.000 -0.5154 0.01179 0.00612 -0.0826 0.8523 0.0283
-7.750 -0.4891 0.01142 0.00566 -0.0823 0.8391 0.0292
-7.500 -0.4622 0.01115 0.00531 -0.0822 0.8261 0.0298
-7.250 -0.4351 0.01091 0.00500 -0.0821 0.8135 0.0304
-7.000 -0.4078 0.01071 0.00472 -0.0819 0.8013 0.0310
-6.750 -0.3804 0.01052 0.00446 -0.0819 0.7898 0.0316
-6.500 -0.3526 0.01034 0.00421 -0.0818 0.7795 0.0323
-6.250 -0.3247 0.01018 0.00399 -0.0818 0.7706 0.0330
-6.000 -0.2968 0.01002 0.00377 -0.0818 0.7616 0.0336
-5.750 -0.2687 0.00986 0.00355 -0.0818 0.7535 0.0341
-5.500 -0.2409 0.00966 0.00330 -0.0818 0.7452 0.0356
-5.250 -0.2127 0.00949 0.00311 -0.0819 0.7382 0.0371
-5.000 -0.1845 0.00934 0.00293 -0.0819 0.7315 0.0386
-4.750 -0.1563 0.00922 0.00277 -0.0820 0.7247 0.0401
-4.500 -0.1279 0.00909 0.00261 -0.0821 0.7166 0.0424
-4.250 -0.0998 0.00896 0.00245 -0.0821 0.7087 0.0460
-4.000 -0.0713 0.00884 0.00232 -0.0822 0.7016 0.0499
-3.750 -0.0432 0.00871 0.00219 -0.0823 0.6947 0.0563
-3.500 -0.0147 0.00859 0.00208 -0.0824 0.6881 0.0635
-3.250 0.0138 0.00849 0.00199 -0.0825 0.6812 0.0716
-3.000 0.0422 0.00841 0.00192 -0.0826 0.6738 0.0798
-2.750 0.0707 0.00834 0.00184 -0.0827 0.6650 0.0861
-2.500 0.0993 0.00829 0.00178 -0.0828 0.6578 0.0915
-2.250 0.1280 0.00826 0.00172 -0.0829 0.6505 0.0941
-2.000 0.1566 0.00821 0.00166 -0.0831 0.6432 0.0990
-1.750 0.1851 0.00817 0.00161 -0.0832 0.6339 0.1039
-1.500 0.2136 0.00816 0.00156 -0.0833 0.6235 0.1076
-1.250 0.2420 0.00815 0.00152 -0.0834 0.6140 0.1121
-1.000 0.2707 0.00809 0.00148 -0.0835 0.6058 0.1197
-0.500 0.3277 0.00803 0.00143 -0.0838 0.5894 0.1353
-0.250 0.3561 0.00801 0.00141 -0.0839 0.5814 0.1453
0.000 0.3845 0.00797 0.00140 -0.0840 0.5717 0.1638
0.250 0.4127 0.00793 0.00141 -0.0841 0.5613 0.1870
0.500 0.4407 0.00790 0.00142 -0.0842 0.5492 0.2141
0.750 0.4685 0.00788 0.00144 -0.0842 0.5357 0.2455
1.000 0.4962 0.00786 0.00147 -0.0843 0.5202 0.2831
1.250 0.5236 0.00785 0.00151 -0.0843 0.5008 0.3299
1.500 0.5500 0.00785 0.00159 -0.0842 0.4748 0.3972
1.750 0.5750 0.00787 0.00172 -0.0838 0.4355 0.4983
2.000 0.5992 0.00794 0.00189 -0.0834 0.3930 0.6038
2.250 0.6238 0.00796 0.00204 -0.0829 0.3642 0.7008
2.500 0.6484 0.00790 0.00218 -0.0823 0.3461 0.7918
2.750 0.6690 0.00777 0.00234 -0.0805 0.3316 0.9125
3.000 0.7061 0.00790 0.00248 -0.0825 0.3189 0.9862
3.250 0.7465 0.00807 0.00260 -0.0854 0.3082 1.0000
3.500 0.7718 0.00823 0.00271 -0.0849 0.2997 1.0000
3.750 0.7975 0.00837 0.00281 -0.0845 0.2914 1.0000
4.000 0.8231 0.00853 0.00293 -0.0841 0.2821 1.0000
4.250 0.8485 0.00873 0.00306 -0.0837 0.2696 1.0000
4.500 0.8734 0.00898 0.00322 -0.0832 0.2497 1.0000
4.750 0.8951 0.00948 0.00349 -0.0823 0.2039 1.0000
5.000 0.9182 0.00988 0.00376 -0.0815 0.1800 1.0000
5.250 0.9429 0.01014 0.00396 -0.0810 0.1707 1.0000
5.500 0.9686 0.01033 0.00414 -0.0807 0.1667 1.0000
5.750 0.9939 0.01054 0.00434 -0.0803 0.1628 1.0000
6.000 1.0190 0.01077 0.00455 -0.0799 0.1583 1.0000
6.250 1.0444 0.01097 0.00475 -0.0795 0.1547 1.0000
6.500 1.0698 0.01116 0.00495 -0.0792 0.1511 1.0000
6.750 1.0942 0.01143 0.00519 -0.0786 0.1450 1.0000
7.000 1.1186 0.01168 0.00543 -0.0781 0.1399 1.0000
7.250 1.1434 0.01189 0.00565 -0.0777 0.1344 1.0000
7.500 1.1662 0.01224 0.00593 -0.0770 0.1204 1.0000
8.000 1.2071 0.01323 0.00668 -0.0747 0.0846 1.0000
8.250 1.2285 0.01363 0.00705 -0.0738 0.0779 1.0000
8.500 1.2507 0.01395 0.00739 -0.0729 0.0736 1.0000
8.750 1.2712 0.01437 0.00779 -0.0718 0.0683 1.0000
9.000 1.2921 0.01473 0.00815 -0.0708 0.0632 1.0000
9.250 1.3047 0.01552 0.00879 -0.0684 0.0413 1.0000
9.500 1.3146 0.01633 0.00950 -0.0655 0.0273 1.0000
9.750 1.3287 0.01694 0.01011 -0.0634 0.0217 1.0000
10.000 1.3443 0.01751 0.01068 -0.0616 0.0187 1.0000
10.250 1.3598 0.01810 0.01128 -0.0599 0.0166 1.0000
10.500 1.3756 0.01869 0.01189 -0.0582 0.0152 1.0000
10.750 1.3903 0.01936 0.01258 -0.0565 0.0138 1.0000
11.000 1.4057 0.02000 0.01326 -0.0550 0.0130 1.0000
11.250 1.4208 0.02068 0.01397 -0.0535 0.0123 1.0000
11.500 1.4348 0.02144 0.01476 -0.0519 0.0116 1.0000
11.750 1.4481 0.02228 0.01563 -0.0503 0.0109 1.0000
12.000 1.4605 0.02320 0.01659 -0.0487 0.0104 1.0000
12.250 1.4740 0.02406 0.01751 -0.0473 0.0101 1.0000
12.500 1.4868 0.02500 0.01850 -0.0459 0.0097 1.0000
12.750 1.4989 0.02602 0.01957 -0.0446 0.0094 1.0000
13.000 1.5100 0.02713 0.02072 -0.0432 0.0090 1.0000
13.250 1.5203 0.02835 0.02199 -0.0419 0.0087 1.0000
13.500 1.5295 0.02970 0.02339 -0.0406 0.0083 1.0000
13.750 1.5368 0.03123 0.02498 -0.0393 0.0080 1.0000
14.000 1.5461 0.03264 0.02646 -0.0382 0.0078 1.0000
14.250 1.5547 0.03415 0.02803 -0.0372 0.0076 1.0000
14.500 1.5622 0.03579 0.02974 -0.0362 0.0074 1.0000
14.750 1.5689 0.03753 0.03155 -0.0353 0.0072 1.0000
15.000 1.5746 0.03940 0.03349 -0.0344 0.0071 1.0000
15.250 1.5796 0.04141 0.03557 -0.0336 0.0069 1.0000
15.500 1.5836 0.04355 0.03779 -0.0330 0.0067 1.0000
15.750 1.5866 0.04585 0.04015 -0.0323 0.0066 1.0000
16.000 1.5885 0.04833 0.04271 -0.0318 0.0064 1.0000
16.250 1.5893 0.05100 0.04546 -0.0314 0.0063 1.0000
16.500 1.5885 0.05393 0.04847 -0.0311 0.0062 1.0000
16.750 1.5856 0.05716 0.05179 -0.0309 0.0060 1.0000
17.000 1.5809 0.06072 0.05545 -0.0310 0.0059 1.0000
17.250 1.5789 0.06404 0.05886 -0.0311 0.0059 1.0000
17.500 1.5756 0.06762 0.06254 -0.0315 0.0058 1.0000
17.750 1.5706 0.07147 0.06649 -0.0320 0.0058 1.0000
18.000 1.5647 0.07555 0.07068 -0.0326 0.0057 1.0000
18.250 1.5578 0.07987 0.07510 -0.0335 0.0056 1.0000
18.500 1.5495 0.08450 0.07985 -0.0346 0.0056 1.0000
18.750 1.5397 0.08942 0.08487 -0.0359 0.0055 1.0000
19.000 1.5292 0.09452 0.09009 -0.0373 0.0055 1.0000
19.250 1.5169 0.10004 0.09572 -0.0391 0.0054 1.0000
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