GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 100,000 Max Cl/Cd: 60.3 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe173-il-100000-n5.txt Download as CSV file: xf-goe173-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2688 0.11127 0.10679 -0.0309 1.0000 0.0270
-8.000 -0.2714 0.10943 0.10504 -0.0303 1.0000 0.0270
-7.500 -0.2727 0.10537 0.10115 -0.0306 1.0000 0.0271
-7.250 -0.2660 0.09899 0.09481 -0.0260 1.0000 0.0278
-7.000 -0.2658 0.09621 0.09210 -0.0238 1.0000 0.0285
-6.750 -0.2505 0.09260 0.08852 -0.0267 0.9950 0.0296
-6.500 -0.2244 0.08831 0.08423 -0.0331 0.9857 0.0309
-6.250 -0.1979 0.08412 0.08003 -0.0398 0.9747 0.0320
-6.000 -0.1702 0.07997 0.07586 -0.0468 0.9624 0.0333
-5.750 -0.1378 0.07588 0.07172 -0.0554 0.9491 0.0350
-5.500 -0.0896 0.07194 0.06765 -0.0697 0.9347 0.0364
-5.250 -0.0481 0.06766 0.06319 -0.0791 0.9234 0.0367
-5.000 -0.0297 0.06236 0.05793 -0.0808 0.9127 0.0375
-4.750 -0.0134 0.05902 0.05460 -0.0805 0.9016 0.0404
-4.500 0.0503 0.05578 0.05095 -0.0945 0.8898 0.0483
-4.250 0.0695 0.05078 0.04601 -0.0958 0.8806 0.0502
-4.000 0.0967 0.04767 0.04283 -0.0980 0.8698 0.0540
-3.750 0.1482 0.04396 0.03866 -0.1065 0.8589 0.0626
-3.500 0.1702 0.04106 0.03578 -0.1071 0.8484 0.0676
-3.000 0.2543 0.03259 0.02644 -0.1151 0.8271 0.0443
-2.750 0.2900 0.02954 0.02294 -0.1172 0.8146 0.0440
-2.500 0.3251 0.02688 0.01974 -0.1186 0.8018 0.0457
-2.250 0.3580 0.02454 0.01688 -0.1195 0.7887 0.0454
-2.000 0.3907 0.02306 0.01474 -0.1198 0.7758 0.0486
-1.750 0.4203 0.02131 0.01259 -0.1200 0.7628 0.0494
-1.250 0.4769 0.01930 0.00999 -0.1197 0.7361 0.0530
-1.000 0.5045 0.01866 0.00915 -0.1194 0.7236 0.0562
-0.750 0.5320 0.01799 0.00826 -0.1190 0.7120 0.0566
-0.500 0.5593 0.01744 0.00755 -0.1186 0.7006 0.0572
-0.250 0.5863 0.01699 0.00698 -0.1181 0.6895 0.0582
0.000 0.6129 0.01665 0.00652 -0.1176 0.6780 0.0596
0.250 0.6391 0.01641 0.00616 -0.1171 0.6655 0.0613
0.500 0.6655 0.01619 0.00587 -0.1166 0.6530 0.0656
0.750 0.6922 0.01611 0.00568 -0.1162 0.6403 0.0746
1.000 0.7190 0.01599 0.00550 -0.1158 0.6271 0.0839
1.250 0.7457 0.01581 0.00542 -0.1154 0.6136 0.1336
1.750 0.7932 0.01438 0.00537 -0.1135 0.5855 1.0000
2.000 0.8189 0.01456 0.00537 -0.1129 0.5695 1.0000
2.250 0.8444 0.01476 0.00540 -0.1123 0.5524 1.0000
2.500 0.8696 0.01498 0.00547 -0.1117 0.5342 1.0000
2.750 0.8945 0.01523 0.00555 -0.1111 0.5156 1.0000
3.000 0.9193 0.01549 0.00570 -0.1105 0.4955 1.0000
3.250 0.9438 0.01579 0.00586 -0.1098 0.4754 1.0000
3.500 0.9680 0.01612 0.00607 -0.1091 0.4558 1.0000
3.750 0.9922 0.01647 0.00631 -0.1085 0.4366 1.0000
4.000 1.0161 0.01685 0.00658 -0.1078 0.4192 1.0000
4.250 1.0399 0.01726 0.00691 -0.1072 0.4042 1.0000
4.500 1.0638 0.01769 0.00726 -0.1065 0.3916 1.0000
4.750 1.0875 0.01814 0.00763 -0.1059 0.3811 1.0000
5.000 1.1115 0.01859 0.00807 -0.1054 0.3720 1.0000
5.250 1.1357 0.01906 0.00853 -0.1048 0.3645 1.0000
5.500 1.1598 0.01954 0.00901 -0.1043 0.3578 1.0000
5.750 1.1840 0.02004 0.00951 -0.1038 0.3522 1.0000
6.000 1.2084 0.02053 0.01010 -0.1034 0.3465 1.0000
6.250 1.2327 0.02106 0.01066 -0.1029 0.3418 1.0000
6.500 1.2571 0.02160 0.01127 -0.1025 0.3371 1.0000
6.750 1.2814 0.02213 0.01193 -0.1021 0.3322 1.0000
7.000 1.3057 0.02270 0.01262 -0.1016 0.3280 1.0000
7.250 1.3279 0.02323 0.01326 -0.1009 0.3198 1.0000
7.500 1.3474 0.02371 0.01380 -0.0997 0.3071 1.0000
7.750 1.3670 0.02421 0.01436 -0.0986 0.2959 1.0000
8.000 1.3849 0.02464 0.01500 -0.0972 0.2821 1.0000
8.250 1.3998 0.02507 0.01554 -0.0954 0.2611 1.0000
8.500 1.4165 0.02557 0.01618 -0.0938 0.2424 1.0000
8.750 1.4311 0.02622 0.01689 -0.0920 0.2152 1.0000
9.000 1.4427 0.02722 0.01779 -0.0899 0.1629 1.0000
9.250 1.4200 0.03108 0.02056 -0.0844 0.0531 1.0000
9.500 1.4127 0.03368 0.02296 -0.0805 0.0259 1.0000
9.750 1.4138 0.03560 0.02500 -0.0777 0.0231 1.0000
10.000 1.4131 0.03772 0.02730 -0.0751 0.0209 1.0000
10.250 1.4105 0.04012 0.02991 -0.0728 0.0193 1.0000
10.500 1.4063 0.04284 0.03292 -0.0709 0.0184 1.0000
10.750 1.4001 0.04599 0.03633 -0.0696 0.0178 1.0000
11.000 1.3930 0.04948 0.04004 -0.0688 0.0175 1.0000
11.250 1.3854 0.05327 0.04408 -0.0684 0.0172 1.0000
11.500 1.3757 0.05753 0.04858 -0.0685 0.0171 1.0000
11.750 1.3644 0.06226 0.05353 -0.0690 0.0169 1.0000
12.000 1.3517 0.06739 0.05888 -0.0699 0.0168 1.0000
12.250 1.3381 0.07289 0.06459 -0.0712 0.0167 1.0000
12.500 1.3239 0.07866 0.07055 -0.0726 0.0165 1.0000
12.750 1.3101 0.08458 0.07665 -0.0743 0.0164 1.0000
13.000 1.2973 0.09044 0.08268 -0.0760 0.0163 1.0000
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Polar data table (+)
Polar graphs
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