GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.57 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe173-il-1000000.txt Download as CSV file: xf-goe173-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3004 0.11397 0.11235 -0.0216 1.0000 0.0079
-9.500 -0.2945 0.11088 0.10927 -0.0225 1.0000 0.0085
-8.000 -0.2824 0.09378 0.09231 -0.0242 1.0000 0.0090
-7.750 -0.2718 0.09090 0.08944 -0.0260 0.9988 0.0092
-7.500 -0.2501 0.08717 0.08571 -0.0313 0.9954 0.0094
-7.250 -0.2288 0.08345 0.08199 -0.0366 0.9893 0.0097
-7.000 -0.2021 0.07936 0.07789 -0.0435 0.9826 0.0102
-6.750 -0.1777 0.07529 0.07381 -0.0498 0.9676 0.0110
-6.500 -0.1430 0.07023 0.06867 -0.0600 0.9324 0.0117
-6.250 -0.1189 0.06618 0.06433 -0.0667 0.8597 0.0118
-6.000 -0.0968 0.06247 0.06041 -0.0716 0.8214 0.0119
-5.750 -0.0728 0.05855 0.05633 -0.0765 0.7983 0.0119
-5.500 -0.0482 0.05276 0.05042 -0.0828 0.7813 0.0121
-5.250 -0.0292 0.05061 0.04818 -0.0841 0.7654 0.0124
-5.000 -0.0048 0.04821 0.04569 -0.0868 0.7522 0.0130
-4.750 0.0238 0.04526 0.04262 -0.0905 0.7399 0.0142
-4.500 0.0684 0.04031 0.03746 -0.0973 0.7288 0.0156
-4.250 0.1003 0.03638 0.03337 -0.1006 0.7183 0.0157
-4.000 0.1335 0.02991 0.02661 -0.1050 0.7095 0.0160
-3.750 0.1588 0.02807 0.02464 -0.1062 0.6987 0.0165
-3.500 0.1852 0.02683 0.02330 -0.1070 0.6879 0.0173
-3.250 0.2204 0.02428 0.02047 -0.1077 0.6779 0.0204
-3.000 0.2484 0.02003 0.01589 -0.1094 0.6682 0.0188
-2.750 0.2812 0.01555 0.01082 -0.1100 0.6596 0.0198
-2.500 0.3103 0.01333 0.00815 -0.1103 0.6505 0.0215
-2.250 0.3360 0.01449 0.00951 -0.1104 0.6397 0.0240
-2.000 0.3655 0.01274 0.00743 -0.1105 0.6301 0.0243
-1.750 0.3941 0.01218 0.00659 -0.1104 0.6201 0.0281
-1.500 0.4215 0.01149 0.00584 -0.1105 0.6094 0.0298
-1.250 0.4496 0.01097 0.00520 -0.1105 0.5978 0.0310
-1.000 0.4779 0.01028 0.00435 -0.1104 0.5860 0.0313
-0.750 0.5058 0.00988 0.00383 -0.1103 0.5738 0.0326
-0.500 0.5337 0.00941 0.00324 -0.1101 0.5619 0.0323
-0.250 0.5615 0.00906 0.00280 -0.1100 0.5496 0.0321
0.000 0.5892 0.00880 0.00247 -0.1099 0.5367 0.0322
0.250 0.6168 0.00865 0.00224 -0.1098 0.5228 0.0331
0.500 0.6445 0.00850 0.00202 -0.1097 0.5079 0.0335
0.750 0.6721 0.00843 0.00187 -0.1096 0.4911 0.0343
1.000 0.6995 0.00843 0.00178 -0.1095 0.4704 0.0349
1.250 0.7265 0.00850 0.00173 -0.1093 0.4444 0.0354
1.500 0.7529 0.00866 0.00173 -0.1091 0.4094 0.0356
1.750 0.7790 0.00887 0.00176 -0.1088 0.3750 0.0361
2.250 0.8323 0.00919 0.00184 -0.1084 0.3355 0.0397
2.500 0.8593 0.00931 0.00192 -0.1083 0.3240 0.0460
2.750 0.8790 0.00777 0.00229 -0.1071 0.3162 0.9429
3.000 0.9081 0.00791 0.00238 -0.1074 0.3079 1.0000
3.250 0.9354 0.00805 0.00248 -0.1074 0.3020 1.0000
3.500 0.9624 0.00821 0.00260 -0.1072 0.2960 1.0000
3.750 0.9894 0.00838 0.00274 -0.1071 0.2908 1.0000
4.000 1.0166 0.00852 0.00286 -0.1070 0.2864 1.0000
4.250 1.0434 0.00869 0.00300 -0.1069 0.2818 1.0000
4.500 1.0700 0.00888 0.00317 -0.1067 0.2769 1.0000
4.750 1.0971 0.00900 0.00329 -0.1067 0.2715 1.0000
5.000 1.1235 0.00921 0.00345 -0.1065 0.2647 1.0000
5.250 1.1504 0.00935 0.00360 -0.1064 0.2601 1.0000
5.500 1.1770 0.00951 0.00376 -0.1063 0.2548 1.0000
5.750 1.2032 0.00971 0.00393 -0.1061 0.2473 1.0000
6.000 1.2296 0.00989 0.00409 -0.1059 0.2393 1.0000
6.250 1.2557 0.01008 0.00428 -0.1058 0.2309 1.0000
6.500 1.2811 0.01035 0.00448 -0.1055 0.2166 1.0000
6.750 1.3044 0.01083 0.00477 -0.1049 0.1848 1.0000
7.000 1.3090 0.01340 0.00643 -0.1017 0.0445 1.0000
7.250 1.3283 0.01433 0.00722 -0.1004 0.0146 1.0000
7.500 1.3519 0.01474 0.00770 -0.0998 0.0135 1.0000
7.750 1.3745 0.01524 0.00826 -0.0990 0.0121 1.0000
8.000 1.3954 0.01590 0.00900 -0.0980 0.0106 1.0000
8.250 1.4157 0.01660 0.00979 -0.0969 0.0099 1.0000
8.500 1.4371 0.01713 0.01038 -0.0960 0.0094 1.0000
8.750 1.4574 0.01775 0.01107 -0.0949 0.0089 1.0000
9.000 1.4766 0.01844 0.01183 -0.0937 0.0084 1.0000
9.250 1.4946 0.01917 0.01262 -0.0923 0.0079 1.0000
9.500 1.5108 0.02001 0.01352 -0.0907 0.0074 1.0000
9.750 1.5162 0.02162 0.01527 -0.0875 0.0069 1.0000
10.000 1.5214 0.02290 0.01668 -0.0842 0.0066 1.0000
10.250 1.5320 0.02372 0.01756 -0.0818 0.0065 1.0000
10.500 1.5397 0.02474 0.01867 -0.0791 0.0063 1.0000
10.750 1.5451 0.02597 0.01998 -0.0763 0.0061 1.0000
11.000 1.5483 0.02744 0.02155 -0.0737 0.0060 1.0000
11.250 1.5503 0.02914 0.02334 -0.0713 0.0058 1.0000
11.500 1.5512 0.03111 0.02542 -0.0693 0.0057 1.0000
11.750 1.5515 0.03337 0.02777 -0.0677 0.0056 1.0000
12.000 1.5523 0.03577 0.03028 -0.0666 0.0054 1.0000
12.250 1.5520 0.03846 0.03308 -0.0659 0.0053 1.0000
12.500 1.5509 0.04136 0.03607 -0.0653 0.0052 1.0000
12.750 1.5486 0.04449 0.03930 -0.0649 0.0051 1.0000
13.000 1.5463 0.04772 0.04262 -0.0647 0.0050 1.0000
13.250 1.5423 0.05119 0.04618 -0.0647 0.0049 1.0000
13.500 1.5364 0.05496 0.05005 -0.0646 0.0048 1.0000
13.750 1.5294 0.05892 0.05409 -0.0647 0.0047 1.0000
14.000 1.5212 0.06302 0.05828 -0.0648 0.0047 1.0000
14.250 1.5106 0.06738 0.06272 -0.0647 0.0045 1.0000
14.500 1.4940 0.07148 0.06690 -0.0619 0.0043 1.0000
14.750 1.4909 0.07561 0.07116 -0.0634 0.0043 1.0000
15.000 1.4878 0.07974 0.07541 -0.0646 0.0042 1.0000
15.250 1.4840 0.08393 0.07971 -0.0657 0.0042 1.0000
15.500 1.4794 0.08818 0.08408 -0.0667 0.0041 1.0000
15.750 1.4742 0.09249 0.08851 -0.0676 0.0040 1.0000
16.000 1.4687 0.09691 0.09303 -0.0685 0.0040 1.0000
16.250 1.4626 0.10145 0.09770 -0.0696 0.0040 1.0000
16.500 1.4557 0.10616 0.10253 -0.0708 0.0039 1.0000
16.750 1.4487 0.11102 0.10751 -0.0722 0.0039 1.0000
17.000 1.4412 0.11610 0.11272 -0.0739 0.0038 1.0000
17.250 1.4328 0.12140 0.11815 -0.0759 0.0038 1.0000
17.500 1.4242 0.12692 0.12380 -0.0782 0.0038 1.0000
17.750 1.4146 0.13276 0.12977 -0.0808 0.0038 1.0000
18.000 1.4047 0.13882 0.13597 -0.0838 0.0038 1.0000
18.250 1.3942 0.14520 0.14249 -0.0872 0.0038 1.0000
18.500 1.3837 0.15181 0.14923 -0.0909 0.0038 1.0000
18.750 1.3722 0.15877 0.15633 -0.0950 0.0038 1.0000
19.000 1.3613 0.16581 0.16350 -0.0993 0.0038 1.0000
19.250 1.3490 0.17344 0.17126 -0.1042 0.0038 1.0000
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Polar data table (+)
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