GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 500,000 Max Cl/Cd: 101.65 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe173-il-500000.txt Download as CSV file: xf-goe173-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 173 (ALBATROS 6020) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2693 0.09407 0.09201 -0.0242 1.0000 0.0146
-7.500 -0.2720 0.09215 0.09014 -0.0231 1.0000 0.0150
-7.250 -0.2805 0.09080 0.08885 -0.0209 1.0000 0.0153
-7.000 -0.2524 0.08639 0.08444 -0.0310 0.9953 0.0156
-6.750 -0.2176 0.08128 0.07931 -0.0428 0.9890 0.0157
-6.500 -0.1800 0.07589 0.07389 -0.0535 0.9840 0.0157
-6.250 -0.1468 0.07093 0.06890 -0.0616 0.9749 0.0158
-6.000 -0.1313 0.06618 0.06416 -0.0627 0.9656 0.0162
-5.750 -0.1036 0.06250 0.06045 -0.0673 0.9494 0.0166
-5.500 -0.0683 0.05843 0.05629 -0.0743 0.9267 0.0174
-5.250 -0.0323 0.05428 0.05199 -0.0813 0.8920 0.0188
-5.000 0.0178 0.04961 0.04699 -0.0917 0.8571 0.0204
-4.750 0.0508 0.04588 0.04299 -0.0961 0.8308 0.0205
-4.500 0.0733 0.04063 0.03755 -0.0995 0.8117 0.0210
-4.250 0.0951 0.03826 0.03505 -0.1006 0.7948 0.0215
-4.000 0.1205 0.03596 0.03260 -0.1021 0.7801 0.0221
-3.750 0.1490 0.03345 0.02990 -0.1040 0.7670 0.0234
-3.500 0.1892 0.03066 0.02674 -0.1062 0.7552 0.0268
-3.250 0.2211 0.02776 0.02348 -0.1074 0.7435 0.0271
-3.000 0.2464 0.02333 0.01883 -0.1094 0.7324 0.0286
-2.750 0.2727 0.02206 0.01743 -0.1098 0.7207 0.0301
-2.500 0.3023 0.02049 0.01556 -0.1100 0.7106 0.0339
-2.250 0.3332 0.01781 0.01239 -0.1106 0.7011 0.0376
-2.000 0.3598 0.01695 0.01148 -0.1108 0.6908 0.0403
-1.750 0.3889 0.01792 0.01218 -0.1101 0.6802 0.0472
-1.500 0.4157 0.01513 0.00925 -0.1110 0.6702 0.0533
-1.250 0.4437 0.01442 0.00835 -0.1111 0.6601 0.0641
-1.000 0.4713 0.01398 0.00775 -0.1111 0.6501 0.0770
-0.750 0.5029 0.01235 0.00563 -0.1101 0.6406 0.0478
-0.500 0.5310 0.01115 0.00432 -0.1099 0.6302 0.0439
-0.250 0.5587 0.01066 0.00373 -0.1097 0.6194 0.0436
0.000 0.5862 0.01032 0.00330 -0.1095 0.6078 0.0441
0.500 0.6411 0.00978 0.00261 -0.1091 0.5820 0.0444
0.750 0.6685 0.00964 0.00241 -0.1089 0.5682 0.0451
1.000 0.6959 0.00956 0.00227 -0.1087 0.5538 0.0459
1.250 0.7230 0.00955 0.00218 -0.1085 0.5381 0.0470
1.500 0.7501 0.00955 0.00210 -0.1083 0.5206 0.0491
1.750 0.7771 0.00960 0.00206 -0.1081 0.5001 0.0524
2.000 0.8036 0.00970 0.00209 -0.1078 0.4755 0.0661
2.250 0.8237 0.00811 0.00236 -0.1066 0.4472 1.0000
2.500 0.8491 0.00844 0.00246 -0.1062 0.4108 1.0000
2.750 0.8743 0.00881 0.00260 -0.1058 0.3806 1.0000
3.000 0.8999 0.00913 0.00277 -0.1054 0.3609 1.0000
3.250 0.9258 0.00943 0.00295 -0.1051 0.3470 1.0000
3.750 0.9779 0.00995 0.00334 -0.1046 0.3278 1.0000
4.000 1.0036 0.01025 0.00356 -0.1042 0.3207 1.0000
4.250 1.0301 0.01044 0.00375 -0.1040 0.3148 1.0000
4.500 1.0559 0.01071 0.00400 -0.1037 0.3094 1.0000
4.750 1.0818 0.01098 0.00425 -0.1035 0.3048 1.0000
5.000 1.1081 0.01118 0.00447 -0.1032 0.3004 1.0000
5.250 1.1336 0.01145 0.00471 -0.1029 0.2947 1.0000
5.500 1.1595 0.01168 0.00496 -0.1027 0.2887 1.0000
5.750 1.1855 0.01187 0.00517 -0.1025 0.2825 1.0000
6.000 1.2105 0.01217 0.00544 -0.1021 0.2768 1.0000
6.250 1.2370 0.01230 0.00563 -0.1019 0.2703 1.0000
6.500 1.2623 0.01253 0.00585 -0.1016 0.2610 1.0000
6.750 1.2878 0.01272 0.00604 -0.1014 0.2514 1.0000
7.000 1.3133 0.01292 0.00624 -0.1011 0.2389 1.0000
7.250 1.3377 0.01323 0.00646 -0.1007 0.2179 1.0000
7.500 1.3555 0.01422 0.00701 -0.0995 0.1459 1.0000
7.750 1.3566 0.01702 0.00902 -0.0959 0.0270 1.0000
8.000 1.3758 0.01784 0.00985 -0.0946 0.0188 1.0000
8.250 1.3954 0.01857 0.01068 -0.0933 0.0166 1.0000
8.500 1.4130 0.01948 0.01175 -0.0918 0.0146 1.0000
8.750 1.4313 0.02024 0.01261 -0.0904 0.0140 1.0000
9.000 1.4474 0.02115 0.01364 -0.0887 0.0134 1.0000
9.250 1.4613 0.02217 0.01477 -0.0868 0.0128 1.0000
9.500 1.4725 0.02329 0.01601 -0.0845 0.0123 1.0000
9.750 1.4787 0.02450 0.01733 -0.0813 0.0119 1.0000
10.000 1.4817 0.02589 0.01883 -0.0780 0.0116 1.0000
10.250 1.4823 0.02750 0.02055 -0.0747 0.0113 1.0000
10.500 1.4795 0.02949 0.02267 -0.0716 0.0109 1.0000
10.750 1.4722 0.03207 0.02537 -0.0687 0.0106 1.0000
11.000 1.4616 0.03533 0.02876 -0.0664 0.0103 1.0000
11.250 1.4492 0.03909 0.03264 -0.0645 0.0101 1.0000
11.500 1.4502 0.04168 0.03534 -0.0636 0.0099 1.0000
11.750 1.4528 0.04416 0.03793 -0.0629 0.0098 1.0000
12.000 1.4544 0.04682 0.04069 -0.0622 0.0097 1.0000
12.250 1.4548 0.04962 0.04359 -0.0615 0.0095 1.0000
12.500 1.4549 0.05247 0.04655 -0.0607 0.0094 1.0000
12.750 1.4550 0.05535 0.04953 -0.0600 0.0093 1.0000
13.000 1.4551 0.05822 0.05251 -0.0592 0.0092 1.0000
13.250 1.4553 0.06112 0.05553 -0.0584 0.0091 1.0000
13.500 1.4557 0.06402 0.05854 -0.0576 0.0091 1.0000
13.750 1.4560 0.06698 0.06163 -0.0567 0.0090 1.0000
14.000 1.4561 0.07003 0.06481 -0.0557 0.0091 1.0000
14.250 1.4558 0.07326 0.06818 -0.0547 0.0092 1.0000
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Polar data table (+)
Polar graphs
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