GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 500,000 Max Cl/Cd: 96.98 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe309-il-500000.txt Download as CSV file: xf-goe309-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 309 (MVA H.41) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-3.500 -0.0388 0.01967 0.01460 -0.0523 0.7759 0.0322
-3.250 -0.0131 0.01696 0.01137 -0.0515 0.7670 0.0331
-3.000 0.0144 0.01616 0.01025 -0.0512 0.7572 0.0350
-2.750 0.0402 0.01376 0.00749 -0.0508 0.7482 0.0369
-2.500 0.0674 0.01297 0.00652 -0.0506 0.7391 0.0382
-2.250 0.0951 0.01245 0.00589 -0.0505 0.7293 0.0401
-2.000 0.1228 0.01195 0.00529 -0.0503 0.7203 0.0418
-1.750 0.1502 0.01142 0.00462 -0.0500 0.7113 0.0427
-1.500 0.1778 0.01095 0.00406 -0.0499 0.7013 0.0436
-1.250 0.2052 0.01060 0.00363 -0.0496 0.6918 0.0447
-1.000 0.2327 0.01039 0.00333 -0.0495 0.6821 0.0459
-0.750 0.2597 0.00992 0.00281 -0.0492 0.6718 0.0477
-0.500 0.2870 0.00964 0.00249 -0.0490 0.6614 0.0508
-0.250 0.3145 0.00950 0.00230 -0.0489 0.6503 0.0542
0.000 0.3421 0.00940 0.00213 -0.0488 0.6378 0.0584
0.250 0.3695 0.00925 0.00207 -0.0486 0.6239 0.0890
0.500 0.3971 0.00922 0.00204 -0.0486 0.6091 0.1176
0.750 0.4247 0.00920 0.00199 -0.0486 0.5940 0.1316
1.000 0.4522 0.00918 0.00195 -0.0485 0.5786 0.1448
1.250 0.4795 0.00912 0.00193 -0.0485 0.5626 0.1753
1.500 0.5060 0.00890 0.00199 -0.0485 0.5472 0.3128
1.750 0.5180 0.00738 0.00213 -0.0448 0.5356 0.9526
2.000 0.5909 0.00764 0.00229 -0.0546 0.5183 0.9964
2.250 0.6305 0.00779 0.00233 -0.0573 0.5050 1.0000
2.500 0.6556 0.00791 0.00236 -0.0568 0.4941 1.0000
2.750 0.6808 0.00800 0.00242 -0.0564 0.4839 1.0000
3.000 0.7058 0.00811 0.00248 -0.0559 0.4745 1.0000
3.500 0.7556 0.00836 0.00263 -0.0549 0.4564 1.0000
3.750 0.7804 0.00849 0.00274 -0.0543 0.4479 1.0000
4.000 0.8051 0.00863 0.00285 -0.0538 0.4389 1.0000
4.250 0.8298 0.00877 0.00296 -0.0533 0.4266 1.0000
4.500 0.8544 0.00893 0.00307 -0.0528 0.4126 1.0000
4.750 0.8790 0.00910 0.00321 -0.0523 0.3986 1.0000
5.000 0.9030 0.00932 0.00335 -0.0517 0.3773 1.0000
5.250 0.9271 0.00956 0.00350 -0.0511 0.3527 1.0000
5.500 0.9505 0.00990 0.00369 -0.0505 0.3194 1.0000
5.750 0.9717 0.01051 0.00403 -0.0497 0.2649 1.0000
6.000 0.9913 0.01135 0.00452 -0.0487 0.2079 1.0000
6.250 1.0117 0.01212 0.00501 -0.0478 0.1639 1.0000
6.500 1.0261 0.01356 0.00586 -0.0462 0.0733 1.0000
6.750 1.0431 0.01471 0.00676 -0.0448 0.0215 1.0000
7.000 1.0662 0.01515 0.00730 -0.0441 0.0190 1.0000
7.250 1.0885 0.01567 0.00793 -0.0433 0.0175 1.0000
7.500 1.1098 0.01629 0.00865 -0.0424 0.0164 1.0000
7.750 1.1295 0.01706 0.00954 -0.0413 0.0154 1.0000
8.000 1.1461 0.01809 0.01070 -0.0397 0.0147 1.0000
8.250 1.1601 0.01929 0.01204 -0.0378 0.0142 1.0000
8.500 1.1792 0.01994 0.01275 -0.0367 0.0136 1.0000
8.750 1.1941 0.02089 0.01379 -0.0351 0.0132 1.0000
9.000 1.2062 0.02199 0.01498 -0.0330 0.0129 1.0000
9.250 1.2150 0.02315 0.01623 -0.0305 0.0126 1.0000
9.500 1.2198 0.02441 0.01758 -0.0275 0.0124 1.0000
9.750 1.2241 0.02586 0.01912 -0.0249 0.0122 1.0000
10.000 1.2282 0.02747 0.02082 -0.0225 0.0121 1.0000
10.250 1.2326 0.02924 0.02267 -0.0204 0.0121 1.0000
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Polar data table (+)
Polar graphs
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