GOE 12K AIRFOIL (goe12k-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 12K AIRFOIL (goe12k-il) Reynolds number: 100,000 Max Cl/Cd: 40.7 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe12k-il-100000-n5.txt Download as CSV file: xf-goe12k-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 12K 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3871 0.10135 0.09610 -0.0639 0.9679 0.0467
-9.000 -0.3949 0.09775 0.09254 -0.0643 0.9636 0.0474
-8.750 -0.4013 0.09332 0.08814 -0.0668 0.9600 0.0488
-8.500 -0.4087 0.08853 0.08336 -0.0703 0.9568 0.0490
-8.250 -0.4298 0.08494 0.07982 -0.0699 0.9503 0.0493
-8.000 -0.4410 0.07822 0.07304 -0.0747 0.9459 0.0501
-7.750 -0.4603 0.07248 0.06721 -0.0748 0.9393 0.0506
-7.500 -0.4766 0.06191 0.05620 -0.0785 0.9338 0.0521
-7.250 -0.4814 0.05814 0.05226 -0.0766 0.9289 0.0534
-7.000 -0.4682 0.05800 0.05215 -0.0750 0.9257 0.0549
-6.750 -0.4566 0.05589 0.04990 -0.0744 0.9227 0.0567
-6.500 -0.4448 0.05234 0.04602 -0.0744 0.9201 0.0591
-6.250 -0.4422 0.04860 0.04186 -0.0722 0.9159 0.0617
-6.000 -0.4410 0.04480 0.03746 -0.0691 0.9111 0.0639
-5.750 -0.4298 0.04205 0.03423 -0.0673 0.9083 0.0664
-5.500 -0.4098 0.04075 0.03281 -0.0668 0.9063 0.0682
-5.250 -0.3877 0.03942 0.03128 -0.0664 0.9047 0.0700
-5.000 -0.3754 0.03833 0.02995 -0.0640 0.9014 0.0719
-4.750 -0.3636 0.03724 0.02858 -0.0614 0.8972 0.0742
-4.500 -0.3454 0.03582 0.02677 -0.0598 0.8943 0.0758
-4.250 -0.3240 0.03456 0.02512 -0.0587 0.8922 0.0771
-4.000 -0.3000 0.03373 0.02387 -0.0580 0.8905 0.0791
-3.750 -0.2748 0.03265 0.02260 -0.0579 0.8892 0.0807
-3.500 -0.2565 0.03200 0.02184 -0.0563 0.8867 0.0820
-3.250 -0.2441 0.03153 0.02125 -0.0535 0.8827 0.0827
-3.000 -0.2228 0.03100 0.02060 -0.0524 0.8797 0.0837
-2.750 -0.1986 0.03052 0.02000 -0.0519 0.8775 0.0851
-2.500 -0.1732 0.03012 0.01950 -0.0515 0.8758 0.0869
-2.250 -0.1466 0.02984 0.01912 -0.0515 0.8744 0.0896
-2.000 -0.1187 0.02955 0.01872 -0.0516 0.8732 0.0920
-1.750 -0.1050 0.02943 0.01853 -0.0491 0.8698 0.0930
-1.500 -0.0895 0.02929 0.01833 -0.0469 0.8661 0.0940
-1.250 -0.0681 0.02902 0.01811 -0.0459 0.8634 0.0957
-1.000 -0.0450 0.02887 0.01798 -0.0451 0.8614 0.0981
-0.750 -0.0204 0.02879 0.01791 -0.0447 0.8597 0.1009
-0.500 0.0054 0.02875 0.01786 -0.0445 0.8583 0.1038
-0.250 0.0334 0.02875 0.01781 -0.0446 0.8571 0.1082
0.000 0.0400 0.02886 0.01798 -0.0409 0.8516 0.1122
0.250 0.0619 0.02890 0.01803 -0.0400 0.8482 0.1213
0.500 0.0906 0.02881 0.01802 -0.0403 0.8452 0.1372
1.000 0.2969 0.02749 0.01933 -0.0743 0.8477 1.0000
1.250 0.3255 0.02763 0.01936 -0.0745 0.8447 1.0000
1.500 0.3583 0.02769 0.01934 -0.0754 0.8423 1.0000
1.750 0.3688 0.02806 0.01966 -0.0724 0.8356 1.0000
2.000 0.3938 0.02821 0.01976 -0.0720 0.8312 1.0000
2.250 0.4259 0.02822 0.01973 -0.0728 0.8281 1.0000
2.500 0.4440 0.02844 0.01993 -0.0711 0.8218 1.0000
2.750 0.4680 0.02851 0.02000 -0.0704 0.8161 1.0000
3.000 0.5038 0.02832 0.01980 -0.0716 0.8127 1.0000
3.250 0.5166 0.02859 0.02009 -0.0690 0.8040 1.0000
3.500 0.5455 0.02859 0.02013 -0.0692 0.7999 1.0000
3.750 0.5808 0.02839 0.01996 -0.0703 0.7970 1.0000
4.000 0.5904 0.02878 0.02040 -0.0672 0.7872 1.0000
4.250 0.6249 0.02851 0.02019 -0.0681 0.7833 1.0000
4.500 0.6387 0.02876 0.02052 -0.0657 0.7734 1.0000
4.750 0.6741 0.02831 0.02016 -0.0666 0.7687 1.0000
5.000 0.6955 0.02795 0.01988 -0.0648 0.7559 1.0000
5.250 0.7322 0.02612 0.01811 -0.0643 0.7370 1.0000
5.500 0.7464 0.02540 0.01742 -0.0607 0.7092 1.0000
5.750 0.7598 0.02521 0.01728 -0.0575 0.6781 1.0000
6.000 0.7752 0.02522 0.01734 -0.0549 0.6452 1.0000
6.250 0.8170 0.02371 0.01576 -0.0555 0.5832 1.0000
6.500 0.8827 0.02169 0.01280 -0.0593 0.4648 1.0000
6.750 0.8983 0.02235 0.01317 -0.0572 0.4160 1.0000
7.000 0.9121 0.02306 0.01371 -0.0548 0.3730 1.0000
7.250 0.9242 0.02383 0.01431 -0.0523 0.3206 1.0000
7.500 0.9327 0.02485 0.01495 -0.0494 0.2526 1.0000
7.750 0.9432 0.02593 0.01567 -0.0469 0.2002 1.0000
8.000 0.9561 0.02693 0.01645 -0.0448 0.1681 1.0000
8.250 0.9699 0.02785 0.01728 -0.0428 0.1492 1.0000
8.500 0.9832 0.02878 0.01814 -0.0409 0.1365 1.0000
8.750 0.9973 0.02965 0.01905 -0.0390 0.1268 1.0000
9.000 1.0102 0.03060 0.02000 -0.0369 0.1199 1.0000
9.250 1.0244 0.03148 0.02095 -0.0351 0.1134 1.0000
9.500 1.0361 0.03256 0.02197 -0.0331 0.1078 1.0000
9.750 1.0518 0.03338 0.02294 -0.0315 0.1016 1.0000
10.000 1.0652 0.03434 0.02393 -0.0298 0.0960 1.0000
10.250 1.0792 0.03535 0.02499 -0.0282 0.0905 1.0000
10.500 1.0933 0.03630 0.02603 -0.0266 0.0847 1.0000
10.750 1.1057 0.03747 0.02717 -0.0249 0.0799 1.0000
11.000 1.1200 0.03843 0.02835 -0.0233 0.0743 1.0000
11.250 1.1310 0.03960 0.02954 -0.0216 0.0696 1.0000
11.500 1.1438 0.04078 0.03089 -0.0199 0.0643 1.0000
11.750 1.1545 0.04202 0.03220 -0.0182 0.0599 1.0000
12.000 1.1646 0.04340 0.03368 -0.0165 0.0558 1.0000
12.250 1.1750 0.04477 0.03524 -0.0147 0.0513 1.0000
12.500 1.1816 0.04619 0.03673 -0.0128 0.0482 1.0000
12.750 1.1913 0.04784 0.03857 -0.0111 0.0451 1.0000
13.000 1.1995 0.04953 0.04048 -0.0094 0.0419 1.0000
13.250 1.2047 0.05121 0.04229 -0.0075 0.0396 1.0000
13.500 1.2073 0.05299 0.04414 -0.0057 0.0378 1.0000
13.750 1.2113 0.05520 0.04653 -0.0039 0.0361 1.0000
14.000 1.2147 0.05762 0.04923 -0.0021 0.0346 1.0000
14.250 1.2147 0.06007 0.05195 -0.0004 0.0330 1.0000
14.500 1.2131 0.06263 0.05470 0.0012 0.0319 1.0000
14.750 1.2098 0.06519 0.05739 0.0026 0.0308 1.0000
15.000 1.2058 0.06800 0.06034 0.0038 0.0301 1.0000
15.250 1.2004 0.07099 0.06344 0.0048 0.0293 1.0000
15.500 1.1934 0.07454 0.06716 0.0056 0.0289 1.0000
15.750 1.1803 0.07901 0.07189 0.0061 0.0284 1.0000
16.000 1.1645 0.08405 0.07722 0.0060 0.0281 1.0000
16.250 1.1464 0.08968 0.08312 0.0051 0.0279 1.0000
16.500 1.1248 0.09622 0.08994 0.0032 0.0276 1.0000
16.750 1.1003 0.10387 0.09784 0.0001 0.0276 1.0000
17.000 1.0750 0.11238 0.10658 -0.0042 0.0278 1.0000
17.250 1.0447 0.12271 0.11711 -0.0101 0.0280 1.0000
17.500 1.0099 0.13513 0.12969 -0.0176 0.0284 1.0000
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