GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 371 AIRFOIL (goe371-il) Reynolds number: 200,000 Max Cl/Cd: 82 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe371-il-200000.txt Download as CSV file: xf-goe371-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 371 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3280 0.08907 0.08574 -0.0269 1.0000 0.0298
-7.250 -0.3336 0.08724 0.08399 -0.0251 1.0000 0.0303
-7.000 -0.3398 0.08540 0.08222 -0.0236 1.0000 0.0308
-6.750 -0.3461 0.08362 0.08052 -0.0222 1.0000 0.0311
-6.500 -0.3549 0.08206 0.07903 -0.0205 1.0000 0.0315
-6.250 -0.3651 0.08060 0.07764 -0.0187 1.0000 0.0322
-6.000 -0.3498 0.07712 0.07415 -0.0234 0.9971 0.0334
-5.750 -0.2790 0.07104 0.06783 -0.0474 0.9885 0.0367
-5.500 -0.2554 0.06387 0.06064 -0.0525 0.9842 0.0378
-5.250 -0.2341 0.06039 0.05717 -0.0539 0.9785 0.0392
-5.000 -0.2003 0.05645 0.05314 -0.0594 0.9733 0.0417
-4.750 -0.1342 0.05153 0.04772 -0.0737 0.9675 0.0482
-4.500 -0.1133 0.04580 0.04203 -0.0766 0.9613 0.0501
-4.250 -0.0818 0.04331 0.03953 -0.0795 0.9578 0.0550
-4.000 -0.0380 0.03859 0.03437 -0.0859 0.9516 0.0629
-3.750 -0.0078 0.03619 0.03199 -0.0880 0.9464 0.0673
-3.500 0.0362 0.03265 0.02808 -0.0930 0.9432 0.0780
-3.250 0.0706 0.03046 0.02560 -0.0953 0.9373 0.0913
-3.000 0.1046 0.02868 0.02354 -0.0972 0.9317 0.1051
-2.750 0.1404 0.02662 0.02130 -0.0995 0.9281 0.1196
-2.500 0.1662 0.02473 0.01946 -0.0998 0.9206 0.1281
-2.250 0.1977 0.02306 0.01765 -0.1011 0.9154 0.1520
-2.000 0.2410 0.02024 0.01367 -0.1007 0.9101 0.0896
-1.750 0.2708 0.01722 0.01035 -0.1003 0.9031 0.0696
-1.500 0.3050 0.01585 0.00870 -0.1008 0.8983 0.0673
-1.250 0.3313 0.01502 0.00771 -0.1000 0.8890 0.0670
-1.000 0.3625 0.01410 0.00664 -0.1000 0.8827 0.0654
-0.750 0.3889 0.01347 0.00597 -0.0993 0.8735 0.0653
-0.500 0.4166 0.01292 0.00540 -0.0988 0.8653 0.0662
-0.250 0.4443 0.01245 0.00492 -0.0983 0.8565 0.0680
0.000 0.4700 0.01215 0.00462 -0.0975 0.8460 0.0715
0.250 0.4968 0.01186 0.00431 -0.0968 0.8359 0.0760
0.500 0.5243 0.01158 0.00400 -0.0963 0.8262 0.0826
0.750 0.5499 0.01134 0.00382 -0.0954 0.8140 0.1065
1.000 0.5930 0.00922 0.00372 -0.0987 0.8022 1.0000
1.250 0.6186 0.00927 0.00362 -0.0977 0.7874 1.0000
1.500 0.6439 0.00932 0.00352 -0.0967 0.7707 1.0000
1.750 0.6690 0.00939 0.00344 -0.0956 0.7524 1.0000
2.000 0.6932 0.00947 0.00342 -0.0945 0.7312 1.0000
2.250 0.7181 0.00957 0.00340 -0.0935 0.7106 1.0000
2.500 0.7422 0.00967 0.00341 -0.0924 0.6864 1.0000
2.750 0.7666 0.00979 0.00342 -0.0914 0.6621 1.0000
3.000 0.7910 0.00993 0.00346 -0.0905 0.6378 1.0000
3.250 0.8155 0.01009 0.00355 -0.0896 0.6135 1.0000
3.500 0.8399 0.01030 0.00363 -0.0887 0.5918 1.0000
3.750 0.8644 0.01055 0.00378 -0.0879 0.5724 1.0000
4.000 0.8889 0.01084 0.00397 -0.0872 0.5552 1.0000
4.250 0.9134 0.01115 0.00422 -0.0864 0.5388 1.0000
4.500 0.9378 0.01149 0.00448 -0.0857 0.5234 1.0000
4.750 0.9623 0.01182 0.00477 -0.0850 0.5087 1.0000
5.000 0.9864 0.01216 0.00508 -0.0843 0.4931 1.0000
5.250 1.0099 0.01246 0.00541 -0.0834 0.4746 1.0000
5.500 1.0329 0.01276 0.00571 -0.0824 0.4543 1.0000
5.750 1.0555 0.01309 0.00601 -0.0814 0.4336 1.0000
6.000 1.0778 0.01337 0.00632 -0.0803 0.4093 1.0000
6.250 1.0994 0.01368 0.00666 -0.0791 0.3810 1.0000
6.500 1.1196 0.01406 0.00697 -0.0778 0.3403 1.0000
6.750 1.1375 0.01467 0.00735 -0.0761 0.2911 1.0000
7.000 1.1554 0.01541 0.00790 -0.0746 0.2543 1.0000
7.250 1.1737 0.01616 0.00853 -0.0732 0.2278 1.0000
7.500 1.1919 0.01693 0.00922 -0.0718 0.2058 1.0000
7.750 1.2115 0.01757 0.00986 -0.0706 0.1845 1.0000
8.000 1.2301 0.01826 0.01051 -0.0693 0.1616 1.0000
8.250 1.2488 0.01894 0.01116 -0.0680 0.1300 1.0000
8.500 1.2568 0.02068 0.01237 -0.0653 0.0648 1.0000
8.750 1.2641 0.02249 0.01403 -0.0623 0.0423 1.0000
9.000 1.2738 0.02389 0.01552 -0.0596 0.0365 1.0000
9.250 1.2847 0.02508 0.01682 -0.0571 0.0330 1.0000
9.500 1.2876 0.02665 0.01842 -0.0536 0.0303 1.0000
9.750 1.2930 0.02810 0.01997 -0.0505 0.0288 1.0000
10.000 1.3012 0.02938 0.02138 -0.0479 0.0271 1.0000
10.250 1.3077 0.03094 0.02304 -0.0453 0.0260 1.0000
10.500 1.3145 0.03262 0.02481 -0.0429 0.0251 1.0000
10.750 1.3217 0.03444 0.02674 -0.0408 0.0242 1.0000
11.000 1.3304 0.03651 0.02889 -0.0389 0.0236 1.0000
11.250 1.3420 0.03897 0.03147 -0.0373 0.0230 1.0000
11.500 1.3582 0.04284 0.03554 -0.0364 0.0223 1.0000
11.750 1.3611 0.04509 0.03805 -0.0343 0.0218 1.0000
12.000 1.3632 0.04750 0.04072 -0.0323 0.0215 1.0000
12.250 1.3618 0.05014 0.04363 -0.0304 0.0211 1.0000
12.500 1.3584 0.05338 0.04714 -0.0287 0.0210 1.0000
12.750 1.3518 0.05702 0.05106 -0.0274 0.0210 1.0000
13.000 1.3414 0.06102 0.05534 -0.0264 0.0210 1.0000
13.250 1.3290 0.06537 0.05995 -0.0260 0.0211 1.0000
13.500 1.3140 0.07016 0.06499 -0.0262 0.0211 1.0000
13.750 1.2972 0.07544 0.07051 -0.0272 0.0212 1.0000
14.000 1.2792 0.08116 0.07645 -0.0289 0.0214 1.0000
14.250 1.2598 0.08753 0.08303 -0.0314 0.0215 1.0000
14.500 1.2403 0.09435 0.09004 -0.0347 0.0217 1.0000
14.750 1.2193 0.10190 0.09778 -0.0389 0.0218 1.0000
15.000 1.1988 0.11003 0.10607 -0.0434 0.0220 1.0000
15.250 1.1782 0.11880 0.11499 -0.0484 0.0222 1.0000
15.500 1.1655 0.12608 0.12241 -0.0534 0.0224 1.0000
15.750 1.1483 0.13518 0.13165 -0.0600 0.0226 1.0000
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Polar data table (+)
Polar graphs
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