GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 795 AIRFOIL (goe795-il) Reynolds number: 50,000 Max Cl/Cd: 37.99 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795-il-50000.txt Download as CSV file: xf-goe795-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4527 0.10789 0.10092 -0.0190 1.0000 0.2141
-8.500 -0.4328 0.10266 0.09565 -0.0174 1.0000 0.2223
-8.250 -0.4574 0.10240 0.09558 -0.0189 1.0000 0.2283
-8.000 -0.4352 0.09723 0.09037 -0.0171 1.0000 0.2391
-7.750 -0.4333 0.09401 0.08722 -0.0164 1.0000 0.2479
-7.500 -0.4564 0.09324 0.08664 -0.0162 1.0000 0.2557
-7.250 -0.4523 0.08996 0.08342 -0.0145 1.0000 0.2690
-7.000 -0.4545 0.08728 0.08083 -0.0132 1.0000 0.2831
-6.750 -0.4614 0.08494 0.07860 -0.0124 1.0000 0.2978
-6.500 -0.4414 0.08081 0.07446 -0.0087 1.0000 0.3183
-6.250 -0.4486 0.07865 0.07242 -0.0070 1.0000 0.3381
-6.000 -0.4482 0.07575 0.06961 -0.0048 1.0000 0.3564
-5.750 -0.4431 0.07297 0.06687 -0.0019 1.0000 0.3780
-5.500 -0.4404 0.07018 0.06416 0.0013 1.0000 0.4024
-5.250 -0.4386 0.06763 0.06169 0.0051 1.0000 0.4307
-4.750 -0.4170 0.04814 0.04058 -0.0325 1.0000 0.1598
-4.500 -0.4001 0.04348 0.03543 -0.0323 1.0000 0.1442
-4.250 -0.3839 0.04000 0.03169 -0.0313 1.0000 0.1392
-4.000 -0.3655 0.03629 0.02727 -0.0304 1.0000 0.1340
-3.750 -0.3464 0.03350 0.02402 -0.0291 1.0000 0.1346
-3.500 -0.3267 0.03134 0.02152 -0.0277 1.0000 0.1401
-3.250 -0.3075 0.02966 0.01953 -0.0263 1.0000 0.1541
-3.000 -0.2874 0.02822 0.01771 -0.0249 1.0000 0.1723
-2.750 -0.2662 0.02660 0.01597 -0.0236 1.0000 0.1897
-2.500 -0.2424 0.02509 0.01427 -0.0226 1.0000 0.2076
-2.250 -0.2193 0.02395 0.01302 -0.0216 1.0000 0.2416
-2.000 -0.1923 0.02258 0.01172 -0.0211 1.0000 0.2865
-1.750 -0.1665 0.02136 0.01080 -0.0207 1.0000 0.3605
-1.500 -0.0921 0.01799 0.00941 -0.0276 1.0000 1.0000
-1.250 -0.0744 0.01822 0.00917 -0.0262 1.0000 1.0000
-1.000 -0.0571 0.01848 0.00909 -0.0249 1.0000 1.0000
-0.750 -0.0398 0.01877 0.00909 -0.0236 1.0000 1.0000
-0.500 -0.0225 0.01909 0.00912 -0.0225 1.0000 1.0000
-0.250 -0.0052 0.01944 0.00926 -0.0213 1.0000 1.0000
0.000 0.0122 0.01983 0.00945 -0.0203 1.0000 1.0000
0.250 0.0297 0.02024 0.00969 -0.0194 1.0000 1.0000
0.500 0.0471 0.02068 0.00999 -0.0185 1.0000 1.0000
0.750 0.0646 0.02116 0.01032 -0.0176 1.0000 1.0000
1.000 0.0819 0.02168 0.01073 -0.0169 1.0000 1.0000
1.250 0.0992 0.02223 0.01119 -0.0162 1.0000 1.0000
1.500 0.1164 0.02283 0.01171 -0.0155 1.0000 1.0000
1.750 0.1334 0.02346 0.01229 -0.0150 1.0000 1.0000
2.000 0.1501 0.02415 0.01293 -0.0144 1.0000 1.0000
2.250 0.1719 0.02498 0.01374 -0.0151 0.9976 1.0000
2.500 0.2290 0.02647 0.01525 -0.0225 0.9788 1.0000
2.750 0.2795 0.02766 0.01652 -0.0282 0.9600 1.0000
3.000 0.3318 0.02879 0.01773 -0.0340 0.9413 1.0000
3.250 0.3744 0.02965 0.01871 -0.0379 0.9208 1.0000
3.500 0.4287 0.03051 0.01977 -0.0434 0.9010 1.0000
3.750 0.4666 0.03116 0.02059 -0.0458 0.8781 1.0000
4.000 0.5130 0.03170 0.02135 -0.0493 0.8555 1.0000
4.250 0.5693 0.03188 0.02187 -0.0538 0.8326 1.0000
4.500 0.6314 0.03127 0.02162 -0.0578 0.8048 1.0000
4.750 0.6887 0.03009 0.02081 -0.0599 0.7727 1.0000
5.000 0.7451 0.02862 0.01979 -0.0611 0.7416 1.0000
5.250 0.7989 0.02643 0.01795 -0.0603 0.7023 1.0000
5.500 0.8385 0.02458 0.01626 -0.0574 0.6545 1.0000
5.750 0.8615 0.02375 0.01550 -0.0533 0.6020 1.0000
6.000 0.8798 0.02326 0.01500 -0.0488 0.5393 1.0000
6.250 0.8920 0.02348 0.01486 -0.0439 0.4566 1.0000
6.500 0.8975 0.02503 0.01555 -0.0386 0.3512 1.0000
6.750 0.9065 0.02724 0.01706 -0.0349 0.2685 1.0000
7.000 0.9291 0.02941 0.01880 -0.0334 0.2243 1.0000
7.250 0.9586 0.03179 0.02105 -0.0330 0.1973 1.0000
7.500 0.9802 0.03398 0.02337 -0.0316 0.1741 1.0000
7.750 1.0013 0.03670 0.02616 -0.0303 0.1527 1.0000
8.000 1.0196 0.03949 0.02895 -0.0288 0.1299 1.0000
8.250 1.0332 0.04272 0.03250 -0.0264 0.1143 1.0000
8.500 1.0461 0.04584 0.03582 -0.0242 0.1017 1.0000
8.750 1.0515 0.04946 0.04014 -0.0209 0.0967 1.0000
9.000 1.0580 0.05347 0.04459 -0.0182 0.0940 1.0000
9.250 1.0720 0.05802 0.04916 -0.0170 0.0902 1.0000
9.500 1.0689 0.06233 0.05389 -0.0141 0.0893 1.0000
9.750 1.0589 0.06633 0.05836 -0.0109 0.0888 1.0000
10.000 1.0491 0.07056 0.06290 -0.0084 0.0889 1.0000
10.250 1.0350 0.07481 0.06742 -0.0059 0.0890 1.0000
10.500 1.0197 0.07898 0.07177 -0.0038 0.0892 1.0000
10.750 1.0056 0.08347 0.07636 -0.0021 0.0896 1.0000
11.000 0.9379 0.09003 0.08325 -0.0036 0.1013 1.0000
11.250 0.8777 0.10138 0.09466 -0.0135 0.1103 1.0000
11.500 0.8664 0.10932 0.10255 -0.0173 0.1140 1.0000
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Polar data table (+)
Polar graphs
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