GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 200,000 Max Cl/Cd: 71.09 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe309-il-200000-n5.txt Download as CSV file: xf-goe309-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3421 0.08781 0.08470 -0.0243 1.0000 0.0144
-7.500 -0.3417 0.08455 0.08150 -0.0261 1.0000 0.0143
-7.250 -0.3399 0.08121 0.07821 -0.0279 1.0000 0.0142
-7.000 -0.3222 0.07617 0.07314 -0.0343 0.9855 0.0142
-6.750 -0.2988 0.06993 0.06683 -0.0428 0.9685 0.0150
-6.250 -0.2556 0.05898 0.05566 -0.0531 0.9335 0.0156
-6.000 -0.2388 0.05402 0.05055 -0.0557 0.9139 0.0158
-5.750 -0.2207 0.05032 0.04670 -0.0572 0.8951 0.0162
-5.500 -0.2011 0.04750 0.04372 -0.0581 0.8772 0.0168
-5.250 -0.1804 0.04514 0.04120 -0.0585 0.8606 0.0178
-5.000 -0.1584 0.04218 0.03803 -0.0592 0.8453 0.0198
-4.750 -0.1354 0.03728 0.03275 -0.0599 0.8320 0.0211
-4.500 -0.1120 0.02961 0.02446 -0.0600 0.8210 0.0230
-4.250 -0.0896 0.02523 0.01951 -0.0595 0.8098 0.0258
-4.000 -0.0649 0.02426 0.01830 -0.0592 0.7977 0.0278
-3.750 -0.0396 0.02204 0.01564 -0.0587 0.7869 0.0309
-3.500 -0.0133 0.02003 0.01306 -0.0581 0.7767 0.0343
-3.250 0.0129 0.01837 0.01091 -0.0576 0.7667 0.0364
-3.000 0.0391 0.01748 0.00986 -0.0574 0.7564 0.0392
-2.750 0.0661 0.01664 0.00877 -0.0571 0.7467 0.0407
-2.500 0.0932 0.01588 0.00776 -0.0568 0.7371 0.0419
-2.250 0.1205 0.01530 0.00700 -0.0565 0.7270 0.0437
-2.000 0.1478 0.01479 0.00632 -0.0563 0.7178 0.0454
-1.750 0.1748 0.01423 0.00561 -0.0560 0.7083 0.0458
-1.500 0.2017 0.01376 0.00503 -0.0557 0.6982 0.0463
-1.250 0.2286 0.01338 0.00454 -0.0553 0.6885 0.0470
-1.000 0.2554 0.01308 0.00415 -0.0550 0.6788 0.0480
-0.750 0.2822 0.01277 0.00379 -0.0548 0.6685 0.0503
-0.500 0.3090 0.01255 0.00354 -0.0545 0.6583 0.0549
-0.250 0.3359 0.01240 0.00335 -0.0543 0.6479 0.0629
0.000 0.3631 0.01229 0.00330 -0.0541 0.6369 0.0856
0.250 0.3903 0.01224 0.00322 -0.0540 0.6261 0.1052
0.500 0.4173 0.01219 0.00314 -0.0539 0.6151 0.1208
1.000 0.4701 0.01193 0.00308 -0.0535 0.5924 0.1967
1.250 0.4949 0.01154 0.00307 -0.0532 0.5801 0.3581
1.500 0.5328 0.01035 0.00323 -0.0545 0.5655 0.9720
1.750 0.5882 0.01051 0.00321 -0.0606 0.5465 0.9997
2.000 0.6132 0.01064 0.00321 -0.0601 0.5300 1.0000
2.250 0.6376 0.01079 0.00323 -0.0594 0.5139 1.0000
2.500 0.6621 0.01095 0.00328 -0.0588 0.5002 1.0000
2.750 0.6867 0.01110 0.00335 -0.0583 0.4896 1.0000
3.000 0.7115 0.01125 0.00346 -0.0577 0.4800 1.0000
3.250 0.7361 0.01142 0.00357 -0.0572 0.4708 1.0000
3.500 0.7607 0.01160 0.00370 -0.0567 0.4611 1.0000
3.750 0.7854 0.01177 0.00385 -0.0561 0.4513 1.0000
4.000 0.8100 0.01197 0.00402 -0.0556 0.4417 1.0000
4.250 0.8346 0.01217 0.00420 -0.0551 0.4317 1.0000
4.500 0.8594 0.01236 0.00440 -0.0547 0.4221 1.0000
4.750 0.8841 0.01258 0.00463 -0.0542 0.4130 1.0000
5.000 0.9083 0.01282 0.00485 -0.0537 0.3977 1.0000
5.250 0.9313 0.01312 0.00506 -0.0530 0.3697 1.0000
5.500 0.9548 0.01343 0.00531 -0.0524 0.3449 1.0000
5.750 0.9768 0.01387 0.00562 -0.0516 0.3071 1.0000
6.000 0.9973 0.01448 0.00601 -0.0507 0.2644 1.0000
6.250 1.0162 0.01530 0.00655 -0.0497 0.2195 1.0000
6.500 1.0350 0.01613 0.00717 -0.0486 0.1831 1.0000
6.750 1.0524 0.01710 0.00788 -0.0474 0.1364 1.0000
7.000 1.0558 0.01948 0.00951 -0.0445 0.0220 1.0000
7.250 1.0764 0.02008 0.01022 -0.0435 0.0191 1.0000
7.500 1.0961 0.02076 0.01105 -0.0424 0.0172 1.0000
7.750 1.1137 0.02160 0.01205 -0.0410 0.0150 1.0000
8.000 1.1299 0.02255 0.01318 -0.0395 0.0137 1.0000
8.250 1.1435 0.02368 0.01457 -0.0376 0.0129 1.0000
8.500 1.1526 0.02507 0.01617 -0.0353 0.0123 1.0000
8.750 1.1645 0.02606 0.01730 -0.0333 0.0119 1.0000
9.000 1.1726 0.02714 0.01850 -0.0309 0.0112 1.0000
9.250 1.1782 0.02845 0.01993 -0.0285 0.0105 1.0000
9.500 1.1810 0.03008 0.02168 -0.0262 0.0102 1.0000
9.750 1.1825 0.03196 0.02368 -0.0241 0.0099 1.0000
10.000 1.1834 0.03406 0.02588 -0.0225 0.0097 1.0000
10.250 1.1842 0.03634 0.02825 -0.0212 0.0095 1.0000
10.500 1.1853 0.03873 0.03073 -0.0200 0.0093 1.0000
10.750 1.1869 0.04116 0.03323 -0.0190 0.0091 1.0000
11.000 1.1894 0.04357 0.03570 -0.0181 0.0089 1.0000
11.250 1.1928 0.04592 0.03816 -0.0170 0.0088 1.0000
11.500 1.1977 0.04818 0.04046 -0.0159 0.0086 1.0000
11.750 1.2045 0.05031 0.04258 -0.0145 0.0083 1.0000
12.000 1.2164 0.05232 0.04458 -0.0125 0.0079 1.0000
12.250 1.2186 0.05478 0.04726 -0.0124 0.0076 1.0000
12.500 1.2225 0.05727 0.04994 -0.0121 0.0073 1.0000
12.750 1.2275 0.05980 0.05263 -0.0114 0.0071 1.0000
13.000 1.2317 0.06251 0.05550 -0.0108 0.0070 1.0000
13.250 1.2341 0.06547 0.05863 -0.0103 0.0070 1.0000
13.500 1.2343 0.06869 0.06204 -0.0101 0.0069 1.0000
13.750 1.2326 0.07220 0.06573 -0.0101 0.0069 1.0000
14.000 1.2290 0.07599 0.06971 -0.0105 0.0068 1.0000
14.250 1.2234 0.08007 0.07399 -0.0111 0.0068 1.0000
14.500 1.2164 0.08446 0.07858 -0.0121 0.0068 1.0000
14.750 1.2082 0.08916 0.08347 -0.0134 0.0068 1.0000
15.000 1.1989 0.09417 0.08867 -0.0152 0.0068 1.0000
15.250 1.1887 0.09949 0.09418 -0.0173 0.0068 1.0000
15.500 1.1779 0.10515 0.10002 -0.0198 0.0068 1.0000
15.750 1.1666 0.11111 0.10616 -0.0227 0.0069 1.0000
16.000 1.1549 0.11736 0.11259 -0.0259 0.0069 1.0000
16.250 1.1429 0.12392 0.11931 -0.0296 0.0070 1.0000
16.500 1.1310 0.13076 0.12632 -0.0336 0.0070 1.0000
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Polar data table (+)
Polar graphs
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