GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 200,000 Max Cl/Cd: 73.88 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe377-il-200000-n5.txt Download as CSV file: xf-goe377-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3567 0.08872 0.08542 -0.0248 1.0000 0.0178
-7.250 -0.3646 0.08677 0.08355 -0.0233 1.0000 0.0179
-7.000 -0.3708 0.08471 0.08156 -0.0221 1.0000 0.0181
-6.500 -0.3737 0.07977 0.07670 -0.0223 0.9990 0.0189
-6.250 -0.3387 0.07302 0.06986 -0.0346 0.9925 0.0145
-6.000 -0.3139 0.06780 0.06458 -0.0409 0.9877 0.0142
-5.500 -0.2567 0.05729 0.05388 -0.0534 0.9776 0.0142
-5.250 -0.2298 0.05235 0.04882 -0.0581 0.9707 0.0139
-5.000 -0.1955 0.04695 0.04323 -0.0638 0.9663 0.0137
-4.750 -0.1664 0.04195 0.03802 -0.0673 0.9588 0.0137
-4.500 -0.1311 0.03631 0.03205 -0.0713 0.9548 0.0139
-4.250 -0.1017 0.03160 0.02697 -0.0724 0.9481 0.0151
-4.000 -0.0738 0.02691 0.02185 -0.0741 0.9433 0.0163
-3.750 -0.0417 0.02398 0.01852 -0.0754 0.9401 0.0174
-3.500 -0.0169 0.02140 0.01552 -0.0748 0.9328 0.0188
-3.250 0.0146 0.01900 0.01260 -0.0752 0.9287 0.0231
-3.000 0.0446 0.01687 0.00985 -0.0750 0.9236 0.0263
-2.750 0.0733 0.01628 0.00921 -0.0754 0.9175 0.0311
-2.500 0.1066 0.01535 0.00794 -0.0762 0.9133 0.0359
-2.250 0.1332 0.01469 0.00718 -0.0760 0.9056 0.0406
-2.000 0.1647 0.01404 0.00640 -0.0766 0.9002 0.0432
-1.750 0.1926 0.01365 0.00589 -0.0764 0.8922 0.0468
-1.500 0.2230 0.01301 0.00514 -0.0767 0.8857 0.0476
-1.250 0.2494 0.01250 0.00458 -0.0762 0.8764 0.0481
-1.000 0.2773 0.01205 0.00406 -0.0760 0.8656 0.0491
-0.750 0.3039 0.01157 0.00352 -0.0755 0.8512 0.0515
-0.500 0.3305 0.01124 0.00314 -0.0749 0.8348 0.0558
-0.250 0.3573 0.01103 0.00285 -0.0744 0.8192 0.0620
0.000 0.3837 0.01081 0.00261 -0.0739 0.8035 0.0724
0.250 0.4100 0.01061 0.00242 -0.0734 0.7870 0.0973
0.500 0.4323 0.00999 0.00239 -0.0724 0.7696 0.3034
1.250 0.5635 0.00863 0.00220 -0.0825 0.7089 1.0000
1.500 0.5877 0.00877 0.00219 -0.0816 0.6872 1.0000
1.750 0.6115 0.00892 0.00221 -0.0806 0.6641 1.0000
2.000 0.6351 0.00909 0.00227 -0.0796 0.6415 1.0000
2.250 0.6586 0.00928 0.00234 -0.0786 0.6192 1.0000
2.500 0.6819 0.00948 0.00244 -0.0776 0.5969 1.0000
2.750 0.7048 0.00970 0.00255 -0.0765 0.5737 1.0000
3.000 0.7277 0.00994 0.00270 -0.0754 0.5504 1.0000
3.250 0.7502 0.01019 0.00287 -0.0743 0.5272 1.0000
3.500 0.7728 0.01046 0.00305 -0.0732 0.5032 1.0000
3.750 0.7947 0.01076 0.00325 -0.0720 0.4750 1.0000
4.000 0.8164 0.01107 0.00349 -0.0708 0.4454 1.0000
4.250 0.8380 0.01141 0.00373 -0.0696 0.4156 1.0000
4.500 0.8597 0.01175 0.00400 -0.0685 0.3889 1.0000
4.750 0.8810 0.01213 0.00431 -0.0673 0.3627 1.0000
5.000 0.9024 0.01252 0.00464 -0.0661 0.3396 1.0000
5.250 0.9242 0.01290 0.00499 -0.0651 0.3195 1.0000
5.500 0.9452 0.01334 0.00537 -0.0639 0.2954 1.0000
5.750 0.9644 0.01391 0.00576 -0.0625 0.2569 1.0000
6.000 0.9836 0.01450 0.00621 -0.0612 0.2141 1.0000
6.250 1.0026 0.01517 0.00669 -0.0598 0.1649 1.0000
6.500 1.0127 0.01680 0.00764 -0.0573 0.0618 1.0000
6.750 1.0267 0.01811 0.00870 -0.0552 0.0221 1.0000
7.000 1.0448 0.01897 0.00963 -0.0535 0.0168 1.0000
7.250 1.0623 0.01989 0.01076 -0.0517 0.0140 1.0000
7.500 1.0796 0.02075 0.01186 -0.0499 0.0131 1.0000
7.750 1.0948 0.02177 0.01308 -0.0478 0.0122 1.0000
8.000 1.1084 0.02286 0.01432 -0.0456 0.0112 1.0000
8.250 1.1208 0.02401 0.01557 -0.0434 0.0097 1.0000
8.500 1.1299 0.02542 0.01710 -0.0407 0.0092 1.0000
8.750 1.1356 0.02719 0.01900 -0.0375 0.0088 1.0000
9.000 1.1394 0.02948 0.02140 -0.0342 0.0084 1.0000
9.250 1.1503 0.03112 0.02317 -0.0318 0.0083 1.0000
9.500 1.1619 0.03285 0.02507 -0.0297 0.0081 1.0000
9.750 1.1732 0.03475 0.02715 -0.0276 0.0079 1.0000
10.000 1.1832 0.03675 0.02936 -0.0254 0.0077 1.0000
10.250 1.1908 0.03873 0.03158 -0.0231 0.0074 1.0000
10.500 1.1958 0.04039 0.03352 -0.0207 0.0068 1.0000
10.750 1.1989 0.04201 0.03529 -0.0185 0.0062 1.0000
11.000 1.1994 0.04478 0.03833 -0.0161 0.0063 1.0000
11.250 1.1979 0.04722 0.04098 -0.0141 0.0061 1.0000
11.500 1.1940 0.04998 0.04394 -0.0123 0.0060 1.0000
11.750 1.1872 0.05315 0.04736 -0.0108 0.0060 1.0000
12.000 1.1794 0.05641 0.05081 -0.0098 0.0058 1.0000
12.250 1.1677 0.06050 0.05518 -0.0094 0.0060 1.0000
12.500 1.1563 0.06467 0.05953 -0.0097 0.0058 1.0000
12.750 1.1425 0.06951 0.06461 -0.0107 0.0059 1.0000
13.000 1.1274 0.07491 0.07023 -0.0127 0.0059 1.0000
13.250 1.1122 0.08075 0.07626 -0.0153 0.0059 1.0000
13.500 1.0920 0.08812 0.08388 -0.0193 0.0060 1.0000
13.750 1.0760 0.09516 0.09109 -0.0234 0.0060 1.0000
14.000 1.0573 0.10350 0.09960 -0.0285 0.0061 1.0000
14.250 1.0393 0.11233 0.10858 -0.0340 0.0061 1.0000
14.500 1.0172 0.12319 0.11962 -0.0407 0.0064 1.0000
14.750 0.9985 0.13381 0.13034 -0.0471 0.0065 1.0000
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Polar data table (+)
Polar graphs
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