GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 375 AIRFOIL (goe375-il) Reynolds number: 50,000 Max Cl/Cd: 37.58 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe375-il-50000-n5.txt Download as CSV file: xf-goe375-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 375 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3270 0.10326 0.09665 -0.0168 1.0000 0.0438
-7.750 -0.3265 0.10144 0.09494 -0.0180 1.0000 0.0445
-7.500 -0.3248 0.09971 0.09332 -0.0204 1.0000 0.0450
-7.250 -0.3197 0.09794 0.09163 -0.0238 1.0000 0.0454
-7.000 -0.3122 0.09612 0.08984 -0.0277 1.0000 0.0457
-6.750 -0.3071 0.09074 0.08459 -0.0250 1.0000 0.0467
-6.500 -0.3015 0.08672 0.08064 -0.0229 1.0000 0.0485
-6.250 -0.2953 0.08375 0.07774 -0.0230 1.0000 0.0506
-6.000 -0.2882 0.08104 0.07509 -0.0241 1.0000 0.0531
-5.750 -0.2784 0.07865 0.07274 -0.0266 1.0000 0.0561
-5.500 -0.2578 0.07824 0.07215 -0.0341 1.0000 0.0585
-5.250 -0.2602 0.07288 0.06704 -0.0295 1.0000 0.0607
-5.000 -0.2548 0.06993 0.06413 -0.0282 1.0000 0.0650
-4.750 -0.2408 0.06776 0.06190 -0.0305 1.0000 0.0706
-4.500 -0.2281 0.06496 0.05905 -0.0321 1.0000 0.0743
-4.250 -0.2229 0.06198 0.05616 -0.0303 1.0000 0.0793
-4.000 -0.2042 0.05978 0.05379 -0.0330 1.0000 0.0883
-3.750 -0.1964 0.05697 0.05103 -0.0317 1.0000 0.0962
-3.500 -0.1831 0.05435 0.04837 -0.0321 1.0000 0.1080
-3.250 -0.1658 0.05218 0.04605 -0.0337 1.0000 0.1311
-3.000 -0.1414 0.04860 0.04255 -0.0359 0.9916 0.1785
-2.750 -0.1209 0.04584 0.03988 -0.0369 0.9810 0.2776
-2.500 -0.1064 0.04229 0.03662 -0.0344 0.9707 0.3563
-2.250 -0.0802 0.03929 0.03368 -0.0342 0.9597 0.4161
-1.750 0.0925 0.03417 0.02617 -0.0582 0.9392 0.1370
-1.500 0.1413 0.03240 0.02369 -0.0600 0.9270 0.0981
-1.250 0.1851 0.03047 0.02128 -0.0618 0.9147 0.0835
-1.000 0.2278 0.02872 0.01913 -0.0639 0.9020 0.0826
-0.750 0.2703 0.02712 0.01715 -0.0655 0.8882 0.0783
-0.500 0.3121 0.02593 0.01553 -0.0667 0.8725 0.0746
-0.250 0.3507 0.02460 0.01402 -0.0678 0.8549 0.0783
0.000 0.3923 0.02353 0.01262 -0.0688 0.8359 0.0784
0.250 0.4266 0.02274 0.01160 -0.0686 0.8123 0.0776
0.500 0.4583 0.02209 0.01075 -0.0681 0.7879 0.0775
0.750 0.4874 0.02157 0.01003 -0.0673 0.7623 0.0787
1.000 0.5134 0.02122 0.00953 -0.0662 0.7339 0.0834
1.250 0.5393 0.02097 0.00909 -0.0650 0.7046 0.0861
1.500 0.5653 0.02075 0.00869 -0.0639 0.6748 0.0875
1.750 0.5913 0.02060 0.00833 -0.0628 0.6449 0.0898
2.000 0.6170 0.02057 0.00808 -0.0617 0.6155 0.0934
2.250 0.6421 0.02064 0.00793 -0.0606 0.5866 0.0987
2.500 0.6669 0.02074 0.00792 -0.0595 0.5590 0.1133
2.750 0.6979 0.01938 0.00804 -0.0601 0.5317 1.0000
3.000 0.7222 0.01984 0.00818 -0.0590 0.5071 1.0000
3.250 0.7462 0.02033 0.00843 -0.0581 0.4834 1.0000
3.500 0.7703 0.02085 0.00870 -0.0573 0.4618 1.0000
3.750 0.7942 0.02138 0.00906 -0.0565 0.4403 1.0000
4.000 0.8181 0.02193 0.00945 -0.0557 0.4213 1.0000
4.250 0.8420 0.02250 0.00985 -0.0549 0.4032 1.0000
4.500 0.8655 0.02308 0.01034 -0.0542 0.3856 1.0000
4.750 0.8891 0.02367 0.01085 -0.0535 0.3696 1.0000
5.000 0.9125 0.02428 0.01142 -0.0528 0.3544 1.0000
5.250 0.9358 0.02491 0.01199 -0.0521 0.3408 1.0000
5.500 0.9592 0.02556 0.01259 -0.0514 0.3286 1.0000
5.750 0.9825 0.02624 0.01330 -0.0507 0.3166 1.0000
6.000 1.0056 0.02698 0.01410 -0.0501 0.3053 1.0000
6.250 1.0287 0.02774 0.01491 -0.0494 0.2952 1.0000
6.500 1.0519 0.02849 0.01562 -0.0488 0.2861 1.0000
6.750 1.0741 0.02937 0.01673 -0.0481 0.2762 1.0000
7.000 1.0973 0.03026 0.01766 -0.0475 0.2688 1.0000
7.250 1.1196 0.03129 0.01889 -0.0469 0.2611 1.0000
7.500 1.1427 0.03226 0.01991 -0.0463 0.2549 1.0000
7.750 1.1633 0.03345 0.02144 -0.0455 0.2473 1.0000
8.000 1.1862 0.03442 0.02245 -0.0449 0.2415 1.0000
8.250 1.2047 0.03583 0.02422 -0.0440 0.2347 1.0000
8.500 1.2255 0.03709 0.02570 -0.0433 0.2295 1.0000
8.750 1.2481 0.03834 0.02711 -0.0428 0.2256 1.0000
9.000 1.2629 0.04030 0.02958 -0.0417 0.2209 1.0000
9.250 1.2797 0.04199 0.03161 -0.0407 0.2164 1.0000
9.500 1.3002 0.04332 0.03312 -0.0400 0.2125 1.0000
9.750 1.3124 0.04527 0.03547 -0.0387 0.2080 1.0000
10.000 1.3250 0.04608 0.03654 -0.0372 0.1993 1.0000
10.250 1.3323 0.04685 0.03765 -0.0352 0.1891 1.0000
10.500 1.3417 0.04682 0.03776 -0.0332 0.1780 1.0000
10.750 1.3456 0.04678 0.03786 -0.0308 0.1657 1.0000
11.000 1.3457 0.04823 0.03967 -0.0286 0.1579 1.0000
11.250 1.3442 0.04946 0.04114 -0.0261 0.1509 1.0000
11.500 1.3380 0.05162 0.04364 -0.0240 0.1452 1.0000
11.750 1.3300 0.05361 0.04581 -0.0225 0.1374 1.0000
12.000 1.3155 0.05710 0.04958 -0.0221 0.1302 1.0000
12.250 1.3020 0.06095 0.05359 -0.0226 0.1233 1.0000
12.500 1.2822 0.06675 0.05968 -0.0245 0.1202 1.0000
12.750 1.2593 0.07375 0.06690 -0.0274 0.1195 1.0000
13.000 1.2326 0.08223 0.07553 -0.0313 0.1219 1.0000
13.250 1.2049 0.09149 0.08487 -0.0356 0.1241 1.0000
13.500 1.1782 0.10110 0.09450 -0.0401 0.1255 1.0000
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