GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 100,000 Max Cl/Cd: 58.99 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe174-il-100000-n5.txt Download as CSV file: xf-goe174-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 174 (ALBATROS 5020) 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2796 0.09342 0.08906 -0.0256 1.0000 0.0418
-7.000 -0.2844 0.09158 0.08732 -0.0246 1.0000 0.0427
-6.750 -0.2908 0.08990 0.08574 -0.0236 1.0000 0.0437
-6.500 -0.2509 0.08521 0.08099 -0.0423 0.9874 0.0469
-6.250 -0.2263 0.07970 0.07545 -0.0485 0.9785 0.0478
-6.000 -0.2128 0.07642 0.07220 -0.0453 0.9720 0.0508
-5.750 -0.1552 0.07190 0.06743 -0.0663 0.9565 0.0587
-5.500 -0.1436 0.06694 0.06257 -0.0646 0.9485 0.0603
-5.250 -0.1194 0.06347 0.05909 -0.0662 0.9404 0.0634
-5.000 -0.0604 0.05839 0.05363 -0.0827 0.9285 0.0726
-4.750 -0.0468 0.05500 0.05037 -0.0802 0.9201 0.0761
-4.500 0.0090 0.05058 0.04551 -0.0925 0.9103 0.0879
-4.250 0.0340 0.04674 0.04169 -0.0938 0.8995 0.0897
-4.000 0.0768 0.04138 0.03601 -0.0997 0.8898 0.0753
-3.750 0.1225 0.03481 0.02888 -0.1054 0.8797 0.0523
-3.500 0.1671 0.02905 0.02209 -0.1098 0.8679 0.0478
-3.250 0.1982 0.02735 0.02029 -0.1112 0.8525 0.0503
-3.000 0.2321 0.02504 0.01746 -0.1125 0.8357 0.0505
-2.750 0.2647 0.02304 0.01488 -0.1132 0.8180 0.0499
-2.500 0.2952 0.02162 0.01301 -0.1134 0.8002 0.0499
-2.250 0.3235 0.02064 0.01175 -0.1133 0.7825 0.0512
-2.000 0.3518 0.01985 0.01072 -0.1131 0.7659 0.0534
-1.750 0.3801 0.01903 0.00964 -0.1128 0.7495 0.0539
-1.500 0.4081 0.01832 0.00872 -0.1125 0.7335 0.0542
-1.250 0.4358 0.01774 0.00796 -0.1121 0.7179 0.0548
-1.000 0.4633 0.01725 0.00733 -0.1117 0.7027 0.0555
-0.750 0.4906 0.01686 0.00680 -0.1113 0.6882 0.0565
-0.500 0.5178 0.01658 0.00638 -0.1109 0.6745 0.0580
-0.250 0.5449 0.01631 0.00601 -0.1105 0.6613 0.0617
0.000 0.5719 0.01618 0.00574 -0.1101 0.6487 0.0656
0.250 0.5987 0.01610 0.00552 -0.1096 0.6360 0.0690
0.500 0.6260 0.01605 0.00537 -0.1092 0.6235 0.0748
0.750 0.6533 0.01595 0.00528 -0.1089 0.6112 0.0979
1.000 0.6802 0.01562 0.00540 -0.1089 0.5993 0.2808
1.500 0.7315 0.01450 0.00544 -0.1076 0.5750 1.0000
1.750 0.7578 0.01472 0.00550 -0.1071 0.5620 1.0000
2.000 0.7839 0.01494 0.00558 -0.1067 0.5489 1.0000
2.250 0.8099 0.01517 0.00569 -0.1062 0.5358 1.0000
2.500 0.8358 0.01540 0.00580 -0.1058 0.5230 1.0000
2.750 0.8615 0.01563 0.00593 -0.1053 0.5100 1.0000
3.000 0.8871 0.01588 0.00609 -0.1048 0.4966 1.0000
3.250 0.9125 0.01613 0.00627 -0.1043 0.4831 1.0000
3.500 0.9379 0.01641 0.00648 -0.1038 0.4703 1.0000
3.750 0.9632 0.01671 0.00672 -0.1033 0.4586 1.0000
4.000 0.9884 0.01703 0.00697 -0.1028 0.4483 1.0000
4.250 1.0135 0.01737 0.00725 -0.1023 0.4378 1.0000
4.500 1.0386 0.01772 0.00760 -0.1019 0.4277 1.0000
4.750 1.0633 0.01809 0.00791 -0.1013 0.4183 1.0000
5.000 1.0879 0.01846 0.00828 -0.1008 0.4086 1.0000
5.250 1.1125 0.01886 0.00867 -0.1003 0.3998 1.0000
5.500 1.1368 0.01927 0.00908 -0.0997 0.3915 1.0000
5.750 1.1610 0.01968 0.00954 -0.0992 0.3828 1.0000
6.000 1.1851 0.02013 0.00995 -0.0986 0.3756 1.0000
6.250 1.2091 0.02055 0.01050 -0.0981 0.3673 1.0000
6.500 1.2324 0.02101 0.01094 -0.0974 0.3594 1.0000
6.750 1.2554 0.02145 0.01149 -0.0967 0.3500 1.0000
7.000 1.2781 0.02192 0.01200 -0.0960 0.3418 1.0000
7.250 1.3007 0.02238 0.01259 -0.0952 0.3335 1.0000
7.500 1.3233 0.02289 0.01318 -0.0945 0.3266 1.0000
7.750 1.3460 0.02339 0.01385 -0.0938 0.3202 1.0000
8.000 1.3684 0.02394 0.01444 -0.0930 0.3146 1.0000
8.250 1.3899 0.02446 0.01523 -0.0921 0.3072 1.0000
8.500 1.4099 0.02498 0.01583 -0.0910 0.2983 1.0000
8.750 1.4273 0.02547 0.01645 -0.0895 0.2851 1.0000
9.000 1.4435 0.02599 0.01710 -0.0879 0.2700 1.0000
9.250 1.4590 0.02656 0.01781 -0.0862 0.2542 1.0000
9.500 1.4735 0.02720 0.01864 -0.0844 0.2340 1.0000
9.750 1.4848 0.02803 0.01950 -0.0823 0.2097 1.0000
10.000 1.4912 0.02921 0.02059 -0.0797 0.1733 1.0000
10.250 1.4853 0.03109 0.02219 -0.0756 0.1362 1.0000
10.500 1.4782 0.03336 0.02430 -0.0719 0.1077 1.0000
10.750 1.4633 0.03645 0.02713 -0.0683 0.0634 1.0000
11.000 1.4501 0.03971 0.03034 -0.0655 0.0532 1.0000
11.250 1.4381 0.04318 0.03393 -0.0636 0.0467 1.0000
11.500 1.4302 0.04655 0.03750 -0.0623 0.0409 1.0000
11.750 1.4190 0.05055 0.04168 -0.0617 0.0373 1.0000
12.000 1.4092 0.05468 0.04602 -0.0616 0.0344 1.0000
12.250 1.3987 0.05919 0.05073 -0.0620 0.0321 1.0000
12.500 1.3860 0.06419 0.05589 -0.0628 0.0305 1.0000
12.750 1.3714 0.06965 0.06150 -0.0639 0.0295 1.0000
13.000 1.3575 0.07517 0.06718 -0.0652 0.0285 1.0000
13.250 1.3434 0.08086 0.07305 -0.0666 0.0277 1.0000
13.500 1.3296 0.08668 0.07903 -0.0683 0.0268 1.0000
13.750 1.3166 0.09251 0.08501 -0.0700 0.0260 1.0000
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Polar data table (+)
Polar graphs
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