GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 177 AIRFOIL (goe177-il) Reynolds number: 100,000 Max Cl/Cd: 58.28 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe177-il-100000.txt Download as CSV file: xf-goe177-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 177 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3187 0.09172 0.08735 -0.0194 1.0000 0.0681
-6.750 -0.3138 0.08897 0.08467 -0.0208 1.0000 0.0703
-6.500 -0.3089 0.08643 0.08219 -0.0233 1.0000 0.0727
-6.250 -0.3007 0.08507 0.08088 -0.0316 1.0000 0.0750
-6.000 -0.2855 0.08310 0.07889 -0.0406 1.0000 0.0757
-5.750 -0.2870 0.07757 0.07349 -0.0339 1.0000 0.0769
-5.500 -0.2828 0.07429 0.07028 -0.0307 1.0000 0.0785
-5.250 -0.2761 0.07152 0.06756 -0.0301 1.0000 0.0808
-5.000 -0.2676 0.06881 0.06488 -0.0311 1.0000 0.0837
-4.750 -0.2322 0.06708 0.06284 -0.0449 1.0000 0.0895
-4.500 -0.2369 0.06278 0.05875 -0.0402 1.0000 0.0906
-4.250 -0.2393 0.06051 0.05658 -0.0361 1.0000 0.0929
-4.000 -0.2346 0.05865 0.05476 -0.0353 1.0000 0.0973
-3.750 -0.1761 0.05306 0.04895 -0.0470 0.9918 0.1073
-3.500 -0.1145 0.04785 0.04346 -0.0581 0.9832 0.1200
-3.250 -0.0612 0.04343 0.03881 -0.0659 0.9727 0.1343
-3.000 -0.0107 0.03996 0.03513 -0.0721 0.9620 0.1574
-2.750 0.0607 0.03202 0.02634 -0.0821 0.9560 0.1093
-2.500 0.1197 0.02498 0.01801 -0.0874 0.9472 0.0805
-2.250 0.1707 0.02237 0.01483 -0.0915 0.9366 0.0938
-2.000 0.2163 0.02034 0.01241 -0.0943 0.9231 0.1125
-1.750 0.2564 0.01880 0.01067 -0.0960 0.9065 0.1396
-1.500 0.2937 0.01764 0.00934 -0.0971 0.8885 0.1656
-1.250 0.3272 0.01693 0.00849 -0.0973 0.8685 0.1890
-1.000 0.3575 0.01623 0.00777 -0.0970 0.8470 0.2059
-0.750 0.3861 0.01568 0.00714 -0.0962 0.8249 0.2203
-0.500 0.4130 0.01526 0.00667 -0.0952 0.8031 0.2421
-0.250 0.4389 0.01489 0.00633 -0.0940 0.7807 0.2762
0.000 0.4640 0.01272 0.00583 -0.0923 0.7609 1.0000
0.250 0.4903 0.01295 0.00563 -0.0914 0.7394 1.0000
0.500 0.5164 0.01320 0.00555 -0.0905 0.7192 1.0000
0.750 0.5424 0.01348 0.00555 -0.0897 0.6997 1.0000
1.000 0.5683 0.01375 0.00561 -0.0890 0.6801 1.0000
1.250 0.5943 0.01404 0.00568 -0.0883 0.6623 1.0000
1.500 0.6205 0.01435 0.00577 -0.0877 0.6455 1.0000
1.750 0.6465 0.01465 0.00594 -0.0872 0.6278 1.0000
2.000 0.6726 0.01497 0.00612 -0.0867 0.6114 1.0000
2.250 0.6989 0.01531 0.00633 -0.0862 0.5963 1.0000
2.500 0.7252 0.01567 0.00660 -0.0858 0.5823 1.0000
2.750 0.7515 0.01602 0.00686 -0.0854 0.5686 1.0000
3.000 0.7774 0.01634 0.00708 -0.0849 0.5541 1.0000
3.250 0.8031 0.01663 0.00728 -0.0844 0.5393 1.0000
3.500 0.8288 0.01691 0.00752 -0.0838 0.5250 1.0000
3.750 0.8546 0.01722 0.00779 -0.0834 0.5121 1.0000
4.000 0.8807 0.01756 0.00808 -0.0830 0.5009 1.0000
4.250 0.9067 0.01787 0.00833 -0.0825 0.4898 1.0000
4.500 0.9323 0.01817 0.00865 -0.0821 0.4780 1.0000
4.750 0.9578 0.01849 0.00908 -0.0817 0.4666 1.0000
5.000 0.9836 0.01885 0.00949 -0.0813 0.4570 1.0000
5.250 1.0094 0.01914 0.00977 -0.0809 0.4472 1.0000
5.500 1.0330 0.01918 0.00987 -0.0800 0.4297 1.0000
5.750 1.0575 0.01936 0.01013 -0.0794 0.4165 1.0000
6.000 1.0812 0.01945 0.01028 -0.0786 0.4003 1.0000
6.250 1.1040 0.01948 0.01032 -0.0776 0.3810 1.0000
6.500 1.1274 0.01966 0.01054 -0.0768 0.3650 1.0000
6.750 1.1504 0.01988 0.01086 -0.0760 0.3468 1.0000
7.000 1.1727 0.02013 0.01123 -0.0751 0.3249 1.0000
7.250 1.1959 0.02052 0.01176 -0.0742 0.3092 1.0000
7.500 1.2183 0.02091 0.01233 -0.0733 0.2843 1.0000
7.750 1.2389 0.02147 0.01293 -0.0722 0.2396 1.0000
8.000 1.2415 0.02433 0.01474 -0.0696 0.0941 1.0000
8.250 1.2447 0.02730 0.01739 -0.0670 0.0530 1.0000
8.500 1.2543 0.02925 0.01958 -0.0647 0.0448 1.0000
8.750 1.2619 0.03113 0.02173 -0.0623 0.0408 1.0000
9.000 1.2622 0.03342 0.02420 -0.0595 0.0388 1.0000
9.250 1.2652 0.03520 0.02615 -0.0567 0.0376 1.0000
9.500 1.2653 0.03712 0.02823 -0.0537 0.0367 1.0000
9.750 1.2656 0.03923 0.03045 -0.0512 0.0359 1.0000
10.000 1.2685 0.04137 0.03267 -0.0489 0.0353 1.0000
10.250 1.2772 0.04341 0.03474 -0.0467 0.0347 1.0000
10.500 1.2952 0.04538 0.03672 -0.0447 0.0342 1.0000
10.750 1.3138 0.04750 0.03893 -0.0431 0.0330 1.0000
11.000 1.3289 0.04978 0.04132 -0.0418 0.0316 1.0000
11.250 1.3508 0.05260 0.04425 -0.0408 0.0309 1.0000
11.500 1.3731 0.05626 0.04832 -0.0397 0.0317 1.0000
11.750 1.3746 0.06002 0.05251 -0.0376 0.0326 1.0000
12.000 1.3691 0.06390 0.05678 -0.0357 0.0335 1.0000
12.250 1.3600 0.06799 0.06121 -0.0343 0.0342 1.0000
12.500 1.3483 0.07235 0.06587 -0.0335 0.0349 1.0000
12.750 1.3348 0.07699 0.07079 -0.0333 0.0355 1.0000
13.000 1.3196 0.08200 0.07605 -0.0339 0.0360 1.0000
13.250 1.3030 0.08735 0.08163 -0.0351 0.0364 1.0000
13.500 1.2856 0.09307 0.08756 -0.0370 0.0369 1.0000
13.750 1.2675 0.09917 0.09385 -0.0394 0.0372 1.0000
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Polar data table (+)
Polar graphs
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