GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 500,000 Max Cl/Cd: 101.53 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795sm-il-500000.txt Download as CSV file: xf-goe795sm-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4587 0.08400 0.08177 -0.0285 1.0000 0.0217
-8.250 -0.4641 0.08060 0.07841 -0.0293 1.0000 0.0218
-8.000 -0.4739 0.07755 0.07541 -0.0295 1.0000 0.0224
-7.750 -0.4861 0.07425 0.07215 -0.0298 1.0000 0.0223
-7.500 -0.4925 0.07018 0.06810 -0.0315 1.0000 0.0228
-7.250 -0.4979 0.06593 0.06384 -0.0330 1.0000 0.0234
-7.000 -0.5025 0.06126 0.05914 -0.0341 1.0000 0.0241
-6.250 -0.4874 0.02650 0.02267 -0.0449 0.9895 0.0166
-6.000 -0.4653 0.02058 0.01592 -0.0452 0.9857 0.0163
-5.750 -0.4349 0.01793 0.01278 -0.0461 0.9835 0.0167
-5.500 -0.4061 0.01653 0.01111 -0.0463 0.9797 0.0178
-5.250 -0.3748 0.01554 0.00991 -0.0471 0.9760 0.0184
-5.000 -0.3455 0.01341 0.00751 -0.0476 0.9733 0.0203
-4.750 -0.3096 0.01296 0.00703 -0.0494 0.9713 0.0229
-4.500 -0.2771 0.01266 0.00666 -0.0503 0.9676 0.0258
-4.250 -0.2483 0.01162 0.00555 -0.0505 0.9629 0.0302
-4.000 -0.2128 0.01131 0.00520 -0.0521 0.9602 0.0349
-3.750 -0.1775 0.01067 0.00454 -0.0538 0.9582 0.0409
-3.500 -0.1440 0.01043 0.00426 -0.0549 0.9545 0.0467
-3.250 -0.1136 0.00990 0.00373 -0.0554 0.9492 0.0540
-3.000 -0.0768 0.00963 0.00342 -0.0573 0.9463 0.0607
-2.750 -0.0399 0.00915 0.00297 -0.0592 0.9437 0.0724
-2.500 -0.0112 0.00880 0.00263 -0.0593 0.9359 0.0846
-2.250 0.0234 0.00836 0.00231 -0.0608 0.9309 0.1165
-2.000 0.0520 0.00784 0.00215 -0.0611 0.9220 0.2153
-1.750 0.0856 0.00748 0.00197 -0.0624 0.9148 0.2783
-1.500 0.1132 0.00709 0.00182 -0.0624 0.9033 0.3616
-1.250 0.1369 0.00654 0.00172 -0.0616 0.8908 0.5093
-1.000 0.1542 0.00585 0.00168 -0.0591 0.8780 0.7087
-0.750 0.2538 0.00537 0.00183 -0.0746 0.8779 0.9524
-0.500 0.2992 0.00555 0.00192 -0.0781 0.8674 0.9800
-0.250 0.3630 0.00566 0.00194 -0.0860 0.8589 0.9960
0.000 0.4032 0.00566 0.00185 -0.0887 0.8458 1.0000
0.250 0.4265 0.00570 0.00180 -0.0876 0.8304 1.0000
0.500 0.4495 0.00574 0.00177 -0.0865 0.8154 1.0000
0.750 0.4725 0.00579 0.00175 -0.0854 0.8004 1.0000
1.000 0.4955 0.00584 0.00174 -0.0842 0.7853 1.0000
1.250 0.5185 0.00590 0.00174 -0.0831 0.7702 1.0000
1.500 0.5413 0.00597 0.00176 -0.0819 0.7539 1.0000
1.750 0.5639 0.00605 0.00177 -0.0806 0.7361 1.0000
2.000 0.5859 0.00615 0.00178 -0.0793 0.7142 1.0000
2.250 0.6078 0.00627 0.00181 -0.0778 0.6913 1.0000
2.500 0.6302 0.00637 0.00187 -0.0766 0.6698 1.0000
2.750 0.6520 0.00652 0.00193 -0.0752 0.6454 1.0000
3.000 0.6738 0.00668 0.00200 -0.0738 0.6204 1.0000
3.250 0.6955 0.00685 0.00210 -0.0724 0.5929 1.0000
3.500 0.7166 0.00706 0.00221 -0.0709 0.5612 1.0000
3.750 0.7373 0.00731 0.00236 -0.0694 0.5258 1.0000
4.000 0.7572 0.00761 0.00251 -0.0677 0.4852 1.0000
4.250 0.7767 0.00797 0.00270 -0.0660 0.4413 1.0000
4.750 0.8145 0.00885 0.00318 -0.0625 0.3442 1.0000
5.000 0.8330 0.00937 0.00348 -0.0607 0.2915 1.0000
5.250 0.8510 0.00994 0.00380 -0.0589 0.2346 1.0000
5.500 0.8682 0.01061 0.00418 -0.0570 0.1762 1.0000
5.750 0.8863 0.01122 0.00458 -0.0553 0.1339 1.0000
6.000 0.9051 0.01178 0.00498 -0.0536 0.1023 1.0000
6.250 0.9244 0.01231 0.00541 -0.0521 0.0771 1.0000
6.500 0.9425 0.01295 0.00591 -0.0503 0.0493 1.0000
6.750 0.9590 0.01376 0.00661 -0.0482 0.0301 1.0000
7.000 0.9755 0.01457 0.00744 -0.0460 0.0234 1.0000
7.250 0.9943 0.01515 0.00810 -0.0443 0.0209 1.0000
7.500 1.0128 0.01575 0.00875 -0.0425 0.0187 1.0000
7.750 1.0287 0.01658 0.00963 -0.0404 0.0171 1.0000
8.000 1.0373 0.01807 0.01128 -0.0369 0.0157 1.0000
8.250 1.0527 0.01898 0.01229 -0.0347 0.0152 1.0000
8.500 1.0704 0.01965 0.01305 -0.0330 0.0145 1.0000
8.750 1.0870 0.02044 0.01391 -0.0311 0.0135 1.0000
9.000 1.1038 0.02112 0.01465 -0.0293 0.0124 1.0000
9.250 1.1177 0.02220 0.01582 -0.0271 0.0119 1.0000
9.500 1.1307 0.02341 0.01713 -0.0248 0.0115 1.0000
9.750 1.1404 0.02536 0.01923 -0.0222 0.0108 1.0000
10.000 1.1472 0.02901 0.02318 -0.0195 0.0103 1.0000
10.250 1.1577 0.03071 0.02509 -0.0171 0.0102 1.0000
10.500 1.1652 0.03221 0.02679 -0.0142 0.0100 1.0000
10.750 1.1682 0.03408 0.02888 -0.0107 0.0099 1.0000
11.000 1.1672 0.03637 0.03142 -0.0071 0.0098 1.0000
11.250 1.1634 0.03873 0.03402 -0.0035 0.0097 1.0000
11.500 1.1567 0.04122 0.03676 -0.0001 0.0096 1.0000
11.750 1.1461 0.04419 0.03997 0.0029 0.0096 1.0000
12.000 1.1338 0.04735 0.04336 0.0053 0.0095 1.0000
12.250 1.1279 0.04980 0.04598 0.0066 0.0091 1.0000
12.500 1.1081 0.05439 0.05081 0.0073 0.0093 1.0000
12.750 1.0930 0.05869 0.05531 0.0070 0.0092 1.0000
13.000 1.0766 0.06363 0.06042 0.0056 0.0092 1.0000
13.250 1.0437 0.07185 0.06885 0.0021 0.0097 1.0000
13.500 1.0375 0.07638 0.07352 -0.0007 0.0092 1.0000
13.750 1.0084 0.08577 0.08308 -0.0064 0.0096 1.0000
14.000 0.9700 0.09841 0.09587 -0.0144 0.0101 1.0000
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Polar data table (+)
Polar graphs
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