GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 200,000 Max Cl/Cd: 75.71 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe173-il-200000-n5.txt Download as CSV file: xf-goe173-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2478 0.10291 0.09963 -0.0280 1.0000 0.0185
-8.000 -0.2475 0.10100 0.09778 -0.0279 1.0000 0.0187
-7.750 -0.2500 0.09934 0.09620 -0.0273 1.0000 0.0189
-7.500 -0.2425 0.09681 0.09372 -0.0301 0.9960 0.0190
-7.250 -0.2195 0.09284 0.08975 -0.0376 0.9863 0.0191
-7.000 -0.1956 0.08874 0.08564 -0.0450 0.9751 0.0192
-6.750 -0.1716 0.08455 0.08145 -0.0515 0.9620 0.0192
-6.500 -0.1463 0.08026 0.07714 -0.0578 0.9476 0.0193
-6.250 -0.1189 0.07581 0.07265 -0.0641 0.9323 0.0193
-6.000 -0.0887 0.07119 0.06798 -0.0709 0.9166 0.0193
-5.500 -0.0351 0.06152 0.05817 -0.0809 0.8835 0.0200
-5.250 -0.0148 0.05874 0.05532 -0.0820 0.8661 0.0215
-4.750 0.0617 0.04928 0.04546 -0.0973 0.8315 0.0190
-4.500 0.0862 0.04591 0.04194 -0.0999 0.8154 0.0183
-4.250 0.1176 0.04215 0.03796 -0.1040 0.8002 0.0180
-4.000 0.1576 0.03739 0.03286 -0.1093 0.7868 0.0189
-3.750 0.1811 0.03580 0.03114 -0.1105 0.7727 0.0215
-3.500 0.2160 0.03183 0.02684 -0.1136 0.7607 0.0212
-3.250 0.2486 0.02858 0.02323 -0.1156 0.7495 0.0216
-3.000 0.2800 0.02599 0.02030 -0.1169 0.7383 0.0238
-2.750 0.3140 0.02260 0.01634 -0.1180 0.7276 0.0259
-2.500 0.3454 0.01993 0.01305 -0.1187 0.7172 0.0280
-2.250 0.3716 0.01927 0.01229 -0.1189 0.7052 0.0309
-2.000 0.4007 0.01780 0.01039 -0.1189 0.6932 0.0325
-1.750 0.4292 0.01681 0.00902 -0.1188 0.6811 0.0349
-1.500 0.4574 0.01627 0.00814 -0.1185 0.6699 0.0366
-1.250 0.4853 0.01527 0.00686 -0.1184 0.6596 0.0373
-1.000 0.5127 0.01447 0.00589 -0.1182 0.6490 0.0383
-0.750 0.5398 0.01402 0.00538 -0.1181 0.6377 0.0409
-0.500 0.5670 0.01363 0.00487 -0.1178 0.6268 0.0417
-0.250 0.5942 0.01329 0.00444 -0.1176 0.6160 0.0419
0.000 0.6212 0.01302 0.00410 -0.1173 0.6043 0.0424
0.250 0.6482 0.01282 0.00382 -0.1171 0.5916 0.0432
0.500 0.6751 0.01269 0.00361 -0.1168 0.5782 0.0443
0.750 0.7019 0.01262 0.00345 -0.1166 0.5642 0.0457
1.000 0.7286 0.01261 0.00333 -0.1163 0.5497 0.0474
1.250 0.7552 0.01261 0.00325 -0.1160 0.5348 0.0508
1.500 0.7816 0.01264 0.00324 -0.1157 0.5187 0.0596
1.750 0.8078 0.01267 0.00326 -0.1154 0.5014 0.0876
2.250 0.8534 0.01134 0.00348 -0.1134 0.4618 1.0000
2.500 0.8785 0.01161 0.00357 -0.1129 0.4376 1.0000
2.750 0.9032 0.01193 0.00369 -0.1124 0.4122 1.0000
3.000 0.9279 0.01227 0.00385 -0.1118 0.3897 1.0000
3.250 0.9524 0.01261 0.00406 -0.1113 0.3722 1.0000
3.500 0.9773 0.01295 0.00428 -0.1109 0.3591 1.0000
3.750 1.0022 0.01328 0.00452 -0.1104 0.3488 1.0000
4.250 1.0520 0.01393 0.00508 -0.1096 0.3327 1.0000
4.500 1.0767 0.01428 0.00538 -0.1091 0.3264 1.0000
4.750 1.1018 0.01459 0.00570 -0.1087 0.3209 1.0000
5.000 1.1267 0.01492 0.00604 -0.1083 0.3157 1.0000
5.250 1.1511 0.01530 0.00640 -0.1079 0.3113 1.0000
5.500 1.1760 0.01562 0.00676 -0.1075 0.3071 1.0000
5.750 1.2009 0.01595 0.00716 -0.1071 0.3027 1.0000
6.000 1.2252 0.01632 0.00757 -0.1066 0.2988 1.0000
6.250 1.2492 0.01673 0.00799 -0.1061 0.2946 1.0000
6.500 1.2733 0.01701 0.00836 -0.1056 0.2858 1.0000
6.750 1.2965 0.01736 0.00876 -0.1050 0.2765 1.0000
7.000 1.3190 0.01773 0.00915 -0.1043 0.2664 1.0000
7.250 1.3422 0.01802 0.00952 -0.1037 0.2541 1.0000
7.500 1.3635 0.01841 0.00989 -0.1028 0.2352 1.0000
7.750 1.3835 0.01893 0.01031 -0.1018 0.2001 1.0000
8.000 1.3799 0.02175 0.01216 -0.0980 0.0692 1.0000
8.250 1.3840 0.02380 0.01390 -0.0948 0.0195 1.0000
8.500 1.3996 0.02468 0.01493 -0.0931 0.0160 1.0000
8.750 1.4132 0.02565 0.01610 -0.0911 0.0142 1.0000
9.000 1.4229 0.02672 0.01736 -0.0886 0.0131 1.0000
9.250 1.4295 0.02800 0.01883 -0.0857 0.0122 1.0000
9.500 1.4315 0.02965 0.02069 -0.0826 0.0113 1.0000
9.750 1.4316 0.03150 0.02274 -0.0796 0.0106 1.0000
10.000 1.4364 0.03307 0.02452 -0.0775 0.0100 1.0000
10.250 1.4371 0.03511 0.02673 -0.0754 0.0097 1.0000
10.500 1.4357 0.03752 0.02931 -0.0736 0.0094 1.0000
10.750 1.4327 0.04030 0.03226 -0.0723 0.0091 1.0000
11.000 1.4284 0.04342 0.03554 -0.0713 0.0089 1.0000
11.250 1.4231 0.04684 0.03911 -0.0707 0.0087 1.0000
11.500 1.4167 0.05051 0.04293 -0.0703 0.0085 1.0000
11.750 1.4097 0.05440 0.04696 -0.0701 0.0084 1.0000
12.000 1.4024 0.05841 0.05110 -0.0701 0.0083 1.0000
12.250 1.3951 0.06248 0.05529 -0.0701 0.0081 1.0000
12.500 1.3881 0.06659 0.05951 -0.0703 0.0080 1.0000
12.750 1.3810 0.07072 0.06374 -0.0705 0.0078 1.0000
13.000 1.3742 0.07483 0.06793 -0.0707 0.0076 1.0000
13.250 1.3678 0.07878 0.07192 -0.0706 0.0073 1.0000
13.500 1.3643 0.08218 0.07536 -0.0701 0.0070 1.0000
13.750 1.3638 0.08581 0.07915 -0.0706 0.0068 1.0000
14.000 1.3638 0.08918 0.08265 -0.0707 0.0066 1.0000
14.250 1.3644 0.09236 0.08599 -0.0705 0.0065 1.0000
14.500 1.3652 0.09553 0.08928 -0.0704 0.0064 1.0000
14.750 1.3659 0.09876 0.09265 -0.0703 0.0062 1.0000
15.000 1.3659 0.10220 0.09624 -0.0704 0.0061 1.0000
15.250 1.3652 0.10586 0.10005 -0.0708 0.0061 1.0000
15.500 1.3630 0.10990 0.10425 -0.0715 0.0060 1.0000
15.750 1.3599 0.11419 0.10871 -0.0726 0.0059 1.0000
16.000 1.3556 0.11880 0.11350 -0.0741 0.0059 1.0000
16.250 1.3505 0.12372 0.11860 -0.0759 0.0059 1.0000
16.500 1.3446 0.12894 0.12401 -0.0782 0.0058 1.0000
16.750 1.3379 0.13450 0.12975 -0.0808 0.0058 1.0000
17.000 1.3306 0.14033 0.13577 -0.0839 0.0058 1.0000
17.250 1.3225 0.14650 0.14212 -0.0873 0.0058 1.0000
17.500 1.3140 0.15298 0.14878 -0.0911 0.0058 1.0000
17.750 1.3053 0.15973 0.15571 -0.0953 0.0059 1.0000
18.000 1.2962 0.16683 0.16297 -0.0999 0.0059 1.0000
18.250 1.2870 0.17425 0.17055 -0.1048 0.0059 1.0000
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