GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.09 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe14k-il-1000000.txt Download as CSV file: xf-goe14k-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8322 0.08139 0.07921 -0.0786 0.9917 0.0095
-15.500 -0.8791 0.06806 0.06574 -0.0873 0.9902 0.0095
-15.250 -0.9112 0.05588 0.05336 -0.0976 0.9887 0.0095
-15.000 -0.9486 0.04296 0.04004 -0.1109 0.9870 0.0094
-14.750 -0.9460 0.03978 0.03676 -0.1138 0.9861 0.0097
-14.500 -0.9605 0.03652 0.03331 -0.1123 0.9819 0.0096
-14.250 -0.9514 0.03516 0.03192 -0.1120 0.9797 0.0100
-14.000 -0.9648 0.03175 0.02820 -0.1100 0.9774 0.0097
-13.750 -0.9502 0.03060 0.02697 -0.1098 0.9765 0.0100
-13.500 -0.9284 0.02997 0.02628 -0.1103 0.9759 0.0104
-13.250 -0.9335 0.02836 0.02451 -0.1060 0.9712 0.0104
-13.000 -0.9260 0.02710 0.02312 -0.1037 0.9682 0.0106
-12.750 -0.9135 0.02586 0.02173 -0.1022 0.9665 0.0107
-12.500 -0.8929 0.02512 0.02088 -0.1019 0.9655 0.0113
-12.250 -0.8765 0.02396 0.01958 -0.1010 0.9645 0.0113
-12.000 -0.8726 0.02320 0.01871 -0.0968 0.9598 0.0115
-11.750 -0.8651 0.02206 0.01740 -0.0936 0.9561 0.0119
-11.500 -0.8490 0.02106 0.01629 -0.0922 0.9544 0.0121
-11.250 -0.8285 0.02028 0.01546 -0.0915 0.9534 0.0128
-11.000 -0.8033 0.01977 0.01491 -0.0916 0.9526 0.0134
-10.750 -0.8033 0.01898 0.01399 -0.0861 0.9467 0.0134
-10.500 -0.7831 0.01847 0.01342 -0.0850 0.9441 0.0139
-10.250 -0.7582 0.01797 0.01284 -0.0848 0.9428 0.0145
-10.000 -0.7328 0.01740 0.01218 -0.0847 0.9418 0.0148
-9.750 -0.7129 0.01623 0.01089 -0.0837 0.9407 0.0159
-9.500 -0.6867 0.01565 0.01028 -0.0838 0.9401 0.0166
-9.250 -0.6589 0.01519 0.00977 -0.0843 0.9395 0.0172
-9.000 -0.6540 0.01482 0.00933 -0.0794 0.9328 0.0177
-8.750 -0.6291 0.01444 0.00890 -0.0790 0.9311 0.0183
-8.500 -0.6040 0.01379 0.00816 -0.0788 0.9299 0.0195
-8.250 -0.5766 0.01325 0.00761 -0.0790 0.9289 0.0209
-8.000 -0.5470 0.01288 0.00720 -0.0798 0.9280 0.0225
-7.750 -0.5164 0.01251 0.00678 -0.0807 0.9272 0.0234
-7.500 -0.4854 0.01194 0.00620 -0.0817 0.9265 0.0261
-7.250 -0.4702 0.01180 0.00605 -0.0791 0.9216 0.0275
-7.000 -0.4436 0.01158 0.00579 -0.0790 0.9191 0.0292
-6.750 -0.4141 0.01120 0.00543 -0.0797 0.9174 0.0329
-6.500 -0.3814 0.01100 0.00522 -0.0810 0.9160 0.0354
-6.250 -0.3476 0.01066 0.00486 -0.0826 0.9149 0.0385
-6.000 -0.3116 0.01047 0.00470 -0.0848 0.9140 0.0420
-5.750 -0.2744 0.01032 0.00453 -0.0872 0.9131 0.0442
-5.500 -0.2363 0.00996 0.00414 -0.0899 0.9123 0.0478
-5.250 -0.2299 0.00989 0.00406 -0.0851 0.9062 0.0496
-5.000 -0.2005 0.00971 0.00387 -0.0857 0.9040 0.0521
-4.750 -0.1675 0.00957 0.00372 -0.0871 0.9024 0.0544
-4.500 -0.1309 0.00940 0.00353 -0.0893 0.9012 0.0555
-4.250 -0.0920 0.00902 0.00312 -0.0922 0.9003 0.0604
-4.000 -0.0528 0.00879 0.00289 -0.0951 0.8993 0.0639
-3.750 -0.0129 0.00861 0.00269 -0.0982 0.8982 0.0669
-3.500 -0.0083 0.00862 0.00269 -0.0929 0.8933 0.0681
-3.250 0.0187 0.00845 0.00252 -0.0929 0.8907 0.0744
-3.000 0.0494 0.00824 0.00238 -0.0938 0.8888 0.0881
-2.750 0.0831 0.00771 0.00222 -0.0957 0.8873 0.1853
-2.500 0.1182 0.00734 0.00212 -0.0978 0.8861 0.2623
-2.250 0.1548 0.00709 0.00206 -0.1003 0.8849 0.3209
-2.000 0.1934 0.00686 0.00202 -0.1032 0.8838 0.3805
-1.750 0.1946 0.00681 0.00207 -0.0970 0.8795 0.4105
-1.500 0.2156 0.00663 0.00205 -0.0957 0.8764 0.4612
-1.250 0.2388 0.00627 0.00200 -0.0949 0.8733 0.5587
-1.000 0.2502 0.00557 0.00195 -0.0914 0.8701 0.7546
-0.750 0.3772 0.00586 0.00275 -0.1144 0.8739 0.9018
-0.500 0.4149 0.00602 0.00290 -0.1167 0.8717 0.9125
-0.250 0.4519 0.00617 0.00303 -0.1188 0.8697 0.9208
0.000 0.4760 0.00642 0.00328 -0.1178 0.8668 0.9284
0.250 0.4933 0.00669 0.00356 -0.1151 0.8617 0.9389
0.500 0.5356 0.00680 0.00360 -0.1183 0.8535 0.9404
0.750 0.5507 0.00698 0.00380 -0.1152 0.8472 0.9467
1.000 0.5802 0.00713 0.00392 -0.1155 0.8412 0.9511
1.250 0.6149 0.00730 0.00409 -0.1169 0.8348 0.9534
1.500 0.6512 0.00747 0.00422 -0.1187 0.8252 0.9567
1.750 0.6624 0.00765 0.00442 -0.1148 0.8163 0.9632
2.000 0.6973 0.00771 0.00446 -0.1163 0.8040 0.9650
2.250 0.7287 0.00777 0.00449 -0.1172 0.7943 0.9670
2.500 0.7492 0.00791 0.00465 -0.1155 0.7837 0.9716
2.750 0.7737 0.00801 0.00475 -0.1147 0.7698 0.9753
3.000 0.7945 0.00810 0.00472 -0.1131 0.7312 0.9783
3.250 0.7880 0.00883 0.00502 -0.1052 0.6335 0.9860
3.500 0.7816 0.01003 0.00542 -0.0982 0.4626 0.9921
3.750 0.7997 0.01079 0.00567 -0.0967 0.3558 0.9964
4.000 0.8275 0.01132 0.00574 -0.0975 0.2544 1.0000
4.250 0.8310 0.01190 0.00603 -0.0926 0.1933 1.0000
4.500 0.8376 0.01238 0.00630 -0.0885 0.1493 1.0000
4.750 0.8479 0.01276 0.00654 -0.0850 0.1177 1.0000
5.000 0.8586 0.01317 0.00681 -0.0817 0.0891 1.0000
5.250 0.8724 0.01346 0.00704 -0.0790 0.0771 1.0000
5.500 0.8868 0.01372 0.00728 -0.0764 0.0690 1.0000
5.750 0.9009 0.01400 0.00753 -0.0738 0.0630 1.0000
6.000 0.9160 0.01426 0.00779 -0.0714 0.0585 1.0000
6.250 0.9325 0.01447 0.00802 -0.0693 0.0555 1.0000
6.500 0.9478 0.01476 0.00829 -0.0669 0.0510 1.0000
6.750 0.9637 0.01502 0.00856 -0.0647 0.0468 1.0000
7.000 0.9792 0.01531 0.00883 -0.0625 0.0418 1.0000
7.250 0.9946 0.01562 0.00913 -0.0602 0.0372 1.0000
7.500 1.0094 0.01598 0.00946 -0.0579 0.0325 1.0000
7.750 1.0250 0.01633 0.00981 -0.0557 0.0289 1.0000
8.000 1.0396 0.01674 0.01021 -0.0533 0.0265 1.0000
8.250 1.0539 0.01718 0.01067 -0.0509 0.0239 1.0000
8.500 1.0693 0.01754 0.01106 -0.0488 0.0226 1.0000
8.750 1.0844 0.01794 0.01147 -0.0466 0.0213 1.0000
9.000 1.0967 0.01857 0.01212 -0.0440 0.0196 1.0000
9.250 1.1121 0.01895 0.01255 -0.0419 0.0188 1.0000
9.500 1.1270 0.01939 0.01303 -0.0398 0.0179 1.0000
9.750 1.1418 0.01985 0.01352 -0.0377 0.0172 1.0000
10.000 1.1553 0.02042 0.01409 -0.0354 0.0161 1.0000
10.250 1.1650 0.02125 0.01498 -0.0325 0.0153 1.0000
10.500 1.1788 0.02179 0.01559 -0.0303 0.0150 1.0000
10.750 1.1914 0.02244 0.01631 -0.0279 0.0147 1.0000
11.000 1.2078 0.02278 0.01668 -0.0263 0.0139 1.0000
11.250 1.2203 0.02342 0.01737 -0.0241 0.0135 1.0000
11.500 1.2320 0.02413 0.01813 -0.0217 0.0131 1.0000
11.750 1.2442 0.02478 0.01882 -0.0196 0.0128 1.0000
12.000 1.2484 0.02608 0.02018 -0.0162 0.0121 1.0000
12.250 1.2545 0.02723 0.02143 -0.0133 0.0118 1.0000
12.500 1.2676 0.02785 0.02212 -0.0113 0.0117 1.0000
12.750 1.2791 0.02860 0.02295 -0.0093 0.0113 1.0000
13.000 1.2893 0.02946 0.02387 -0.0070 0.0111 1.0000
13.250 1.3016 0.03014 0.02460 -0.0053 0.0105 1.0000
13.500 1.3088 0.03123 0.02578 -0.0028 0.0105 1.0000
13.750 1.3181 0.03217 0.02679 -0.0007 0.0103 1.0000
14.000 1.3246 0.03334 0.02802 0.0017 0.0100 1.0000
14.250 1.3274 0.03484 0.02963 0.0044 0.0099 1.0000
14.500 1.3337 0.03603 0.03089 0.0065 0.0097 1.0000
14.750 1.3305 0.03808 0.03303 0.0095 0.0093 1.0000
15.000 1.3277 0.04016 0.03524 0.0123 0.0092 1.0000
15.250 1.3272 0.04208 0.03729 0.0147 0.0090 1.0000
15.500 1.3233 0.04440 0.03975 0.0172 0.0089 1.0000
15.750 1.3320 0.04553 0.04095 0.0185 0.0088 1.0000
16.000 1.3376 0.04699 0.04251 0.0199 0.0084 1.0000
16.250 1.3368 0.04911 0.04473 0.0216 0.0085 1.0000
16.500 1.3279 0.05221 0.04798 0.0236 0.0083 1.0000
16.750 1.3295 0.05428 0.05015 0.0247 0.0081 1.0000
17.000 1.3147 0.05829 0.05432 0.0261 0.0082 1.0000
17.250 1.3048 0.06196 0.05815 0.0269 0.0082 1.0000
17.500 1.2936 0.06599 0.06232 0.0273 0.0083 1.0000
17.750 1.2957 0.06854 0.06493 0.0272 0.0077 1.0000
18.000 1.2743 0.07439 0.07098 0.0265 0.0080 1.0000
18.250 1.2633 0.07917 0.07588 0.0254 0.0079 1.0000
18.500 1.2530 0.08405 0.08088 0.0239 0.0078 1.0000
18.750 1.2425 0.08931 0.08623 0.0218 0.0075 1.0000
19.000 1.1892 0.10234 0.09960 0.0162 0.0080 1.0000
19.250 1.1733 0.10921 0.10658 0.0128 0.0079 1.0000
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