GOE 574 AIRFOIL (goe574-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 574 AIRFOIL (goe574-il) Reynolds number: 100,000 Max Cl/Cd: 55.8 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe574-il-100000-n5.txt Download as CSV file: xf-goe574-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 574 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3303 0.10957 0.10514 -0.0363 1.0000 0.0339
-8.250 -0.3333 0.10696 0.10260 -0.0360 1.0000 0.0339
-8.000 -0.3429 0.10494 0.10069 -0.0356 1.0000 0.0340
-7.750 -0.3264 0.09862 0.09438 -0.0322 1.0000 0.0357
-7.500 -0.3309 0.09630 0.09214 -0.0308 1.0000 0.0361
-7.250 -0.3411 0.09447 0.09041 -0.0291 1.0000 0.0362
-7.000 -0.3249 0.09036 0.08631 -0.0337 0.9942 0.0373
-6.750 -0.3034 0.08554 0.08143 -0.0402 0.9860 0.0390
-6.500 -0.2830 0.08066 0.07652 -0.0467 0.9752 0.0403
-6.250 -0.2641 0.07598 0.07181 -0.0527 0.9618 0.0420
-6.000 -0.2384 0.07104 0.06666 -0.0635 0.9406 0.0452
-5.750 -0.2250 0.06468 0.06026 -0.0641 0.9285 0.0332
-5.500 -0.2033 0.05969 0.05511 -0.0679 0.9149 0.0334
-5.250 -0.1787 0.05453 0.04972 -0.0714 0.9042 0.0335
-5.000 -0.1589 0.05010 0.04514 -0.0730 0.8922 0.0328
-4.750 -0.1355 0.04557 0.04037 -0.0749 0.8809 0.0321
-4.500 -0.1084 0.04073 0.03514 -0.0768 0.8705 0.0319
-4.000 -0.0505 0.03256 0.02601 -0.0796 0.8504 0.0363
-3.750 -0.0195 0.02926 0.02215 -0.0806 0.8396 0.0373
-3.500 0.0159 0.02683 0.01917 -0.0822 0.8289 0.0416
-3.250 0.0551 0.02426 0.01584 -0.0841 0.8182 0.0440
-3.000 0.0925 0.02224 0.01329 -0.0859 0.8052 0.0471
-2.750 0.1295 0.02097 0.01172 -0.0879 0.7913 0.0506
-2.500 0.1656 0.01978 0.01017 -0.0893 0.7769 0.0523
-2.250 0.1999 0.01887 0.00899 -0.0904 0.7622 0.0542
-2.000 0.2327 0.01836 0.00822 -0.0913 0.7469 0.0581
-1.750 0.2628 0.01763 0.00737 -0.0918 0.7315 0.0601
-1.500 0.2913 0.01714 0.00675 -0.0918 0.7160 0.0614
-1.250 0.3187 0.01680 0.00625 -0.0916 0.7005 0.0630
-1.000 0.3460 0.01655 0.00582 -0.0914 0.6854 0.0654
-0.750 0.3737 0.01638 0.00547 -0.0913 0.6711 0.0691
-0.500 0.4024 0.01620 0.00519 -0.0914 0.6574 0.0780
-0.250 0.4326 0.01595 0.00501 -0.0920 0.6443 0.1333
0.250 0.5995 0.01444 0.00510 -0.1167 0.6140 1.0000
0.500 0.6230 0.01461 0.00510 -0.1159 0.6026 1.0000
0.750 0.6464 0.01479 0.00513 -0.1150 0.5923 1.0000
1.000 0.6706 0.01498 0.00516 -0.1143 0.5837 1.0000
1.250 0.6940 0.01518 0.00525 -0.1135 0.5752 1.0000
1.500 0.7179 0.01539 0.00534 -0.1128 0.5678 1.0000
1.750 0.7413 0.01560 0.00548 -0.1120 0.5605 1.0000
2.000 0.7652 0.01582 0.00561 -0.1113 0.5541 1.0000
2.250 0.7882 0.01605 0.00580 -0.1104 0.5473 1.0000
2.500 0.8126 0.01629 0.00597 -0.1098 0.5419 1.0000
2.750 0.8354 0.01654 0.00623 -0.1090 0.5360 1.0000
3.000 0.8592 0.01679 0.00647 -0.1083 0.5311 1.0000
3.250 0.8842 0.01707 0.00672 -0.1079 0.5271 1.0000
3.500 0.9066 0.01735 0.00707 -0.1069 0.5222 1.0000
3.750 0.9299 0.01763 0.00738 -0.1062 0.5175 1.0000
4.000 0.9545 0.01792 0.00768 -0.1057 0.5136 1.0000
4.250 0.9770 0.01824 0.00811 -0.1048 0.5094 1.0000
4.500 0.9997 0.01856 0.00854 -0.1040 0.5053 1.0000
4.750 1.0233 0.01889 0.00895 -0.1033 0.5016 1.0000
5.000 1.0485 0.01923 0.00936 -0.1029 0.4983 1.0000
5.250 1.0683 0.01959 0.00991 -0.1015 0.4935 1.0000
5.500 1.0890 0.01986 0.01028 -0.1001 0.4865 1.0000
5.750 1.1022 0.01989 0.01028 -0.0969 0.4697 1.0000
6.000 1.1062 0.01988 0.01028 -0.0919 0.4457 1.0000
6.250 1.1182 0.02004 0.01055 -0.0887 0.4300 1.0000
6.500 1.1268 0.02021 0.01072 -0.0847 0.4098 1.0000
6.750 1.1310 0.02042 0.01098 -0.0800 0.3814 1.0000
7.000 1.1341 0.02075 0.01132 -0.0751 0.3356 1.0000
7.250 1.1183 0.02189 0.01176 -0.0671 0.2348 1.0000
7.500 1.0976 0.02404 0.01323 -0.0593 0.1402 1.0000
7.750 1.0726 0.02657 0.01515 -0.0513 0.0428 1.0000
8.000 1.0715 0.02790 0.01648 -0.0470 0.0326 1.0000
8.250 1.0732 0.02913 0.01784 -0.0433 0.0290 1.0000
8.500 1.0731 0.03053 0.01938 -0.0397 0.0271 1.0000
8.750 1.0738 0.03197 0.02100 -0.0364 0.0258 1.0000
9.000 1.0734 0.03359 0.02282 -0.0333 0.0240 1.0000
9.250 1.0716 0.03543 0.02489 -0.0306 0.0224 1.0000
9.500 1.0688 0.03751 0.02715 -0.0282 0.0215 1.0000
9.750 1.0637 0.03997 0.02980 -0.0261 0.0208 1.0000
10.000 1.0580 0.04267 0.03268 -0.0244 0.0204 1.0000
10.250 1.0521 0.04557 0.03573 -0.0230 0.0199 1.0000
10.500 1.0468 0.04853 0.03885 -0.0219 0.0197 1.0000
10.750 1.0420 0.05153 0.04197 -0.0209 0.0193 1.0000
11.000 1.0367 0.05454 0.04508 -0.0197 0.0187 1.0000
11.250 1.0370 0.05690 0.04751 -0.0184 0.0184 1.0000
11.500 1.0451 0.05803 0.04852 -0.0152 0.0170 1.0000
11.750 1.0583 0.05926 0.04985 -0.0137 0.0164 1.0000
12.000 1.0784 0.06007 0.05075 -0.0116 0.0158 1.0000
12.250 1.1034 0.06098 0.05176 -0.0096 0.0155 1.0000
12.500 1.1265 0.06251 0.05354 -0.0080 0.0152 1.0000
12.750 1.1465 0.06466 0.05591 -0.0066 0.0151 1.0000
13.000 1.1572 0.06744 0.05894 -0.0055 0.0150 1.0000
13.250 1.1609 0.07041 0.06216 -0.0046 0.0150 1.0000
13.500 1.1593 0.07366 0.06566 -0.0039 0.0147 1.0000
13.750 1.1548 0.07720 0.06945 -0.0035 0.0144 1.0000
14.000 1.1487 0.08090 0.07340 -0.0033 0.0144 1.0000
14.250 1.1398 0.08493 0.07767 -0.0034 0.0142 1.0000
14.500 1.1287 0.08917 0.08214 -0.0040 0.0139 1.0000
14.750 1.1171 0.09369 0.08688 -0.0048 0.0138 1.0000
15.000 1.1038 0.09863 0.09205 -0.0061 0.0138 1.0000
15.250 1.0900 0.10379 0.09741 -0.0078 0.0137 1.0000
15.500 1.0758 0.10930 0.10312 -0.0099 0.0138 1.0000
15.750 1.0618 0.11496 0.10897 -0.0124 0.0139 1.0000
16.000 1.0458 0.12135 0.11554 -0.0155 0.0141 1.0000
16.250 1.0304 0.12794 0.12230 -0.0189 0.0141 1.0000
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Polar data table (+)
Polar graphs
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