GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 602 AIRFOIL (goe602-il) Reynolds number: 500,000 Max Cl/Cd: 93.19 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe602-il-500000-n5.txt Download as CSV file: xf-goe602-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4047 0.10090 0.09862 -0.0367 1.0000 0.0067
-10.250 -0.4072 0.09736 0.09511 -0.0373 1.0000 0.0068
-9.750 -0.6002 0.03362 0.03087 -0.0871 0.9798 0.0063
-9.500 -0.5914 0.02680 0.02333 -0.0907 0.9745 0.0064
-9.250 -0.5740 0.02345 0.01952 -0.0916 0.9695 0.0066
-9.000 -0.5485 0.02139 0.01718 -0.0930 0.9671 0.0070
-8.750 -0.5195 0.02000 0.01557 -0.0944 0.9655 0.0073
-8.500 -0.4972 0.01892 0.01432 -0.0940 0.9604 0.0077
-8.250 -0.4696 0.01780 0.01300 -0.0947 0.9573 0.0081
-8.000 -0.4403 0.01674 0.01174 -0.0956 0.9549 0.0087
-7.750 -0.4096 0.01584 0.01061 -0.0967 0.9529 0.0093
-7.500 -0.3862 0.01492 0.00955 -0.0962 0.9475 0.0102
-7.250 -0.3577 0.01438 0.00893 -0.0966 0.9436 0.0109
-7.000 -0.3270 0.01382 0.00828 -0.0975 0.9406 0.0119
-6.750 -0.2964 0.01328 0.00762 -0.0982 0.9376 0.0131
-6.500 -0.2712 0.01274 0.00699 -0.0978 0.9318 0.0144
-6.250 -0.2406 0.01261 0.00688 -0.0985 0.9277 0.0163
-6.000 -0.2089 0.01233 0.00651 -0.0994 0.9242 0.0183
-5.750 -0.1829 0.01207 0.00617 -0.0990 0.9178 0.0198
-5.500 -0.1546 0.01158 0.00560 -0.0993 0.9125 0.0216
-5.250 -0.1261 0.01141 0.00541 -0.0995 0.9069 0.0238
-5.000 -0.0988 0.01115 0.00509 -0.0994 0.9000 0.0257
-4.750 -0.0703 0.01092 0.00477 -0.0995 0.8936 0.0277
-4.500 -0.0436 0.01072 0.00450 -0.0993 0.8856 0.0289
-4.250 -0.0159 0.01054 0.00424 -0.0992 0.8782 0.0296
-4.000 0.0095 0.01005 0.00366 -0.0988 0.8700 0.0314
-3.750 0.0356 0.00969 0.00324 -0.0984 0.8622 0.0332
-3.500 0.0624 0.00944 0.00294 -0.0982 0.8540 0.0352
-3.250 0.0887 0.00924 0.00268 -0.0978 0.8448 0.0366
-3.000 0.1156 0.00907 0.00243 -0.0975 0.8357 0.0381
-2.750 0.1424 0.00893 0.00221 -0.0973 0.8255 0.0395
-2.500 0.1690 0.00881 0.00203 -0.0969 0.8143 0.0408
-2.250 0.1956 0.00870 0.00185 -0.0966 0.8025 0.0436
-2.000 0.2219 0.00858 0.00171 -0.0962 0.7896 0.0504
-1.750 0.2477 0.00840 0.00159 -0.0958 0.7761 0.0825
-1.500 0.2732 0.00821 0.00149 -0.0954 0.7618 0.1288
-1.000 0.3227 0.00774 0.00138 -0.0943 0.7320 0.2887
-0.750 0.3478 0.00763 0.00134 -0.0938 0.7170 0.3382
-0.500 0.3729 0.00754 0.00132 -0.0933 0.7019 0.3834
-0.250 0.3973 0.00739 0.00133 -0.0927 0.6867 0.4569
0.000 0.4207 0.00720 0.00136 -0.0918 0.6712 0.5531
0.250 0.4435 0.00704 0.00141 -0.0908 0.6553 0.6497
0.500 0.4635 0.00682 0.00148 -0.0890 0.6360 0.7606
0.750 0.4944 0.00660 0.00162 -0.0891 0.6126 0.9437
1.000 0.5375 0.00680 0.00165 -0.0926 0.5816 0.9779
1.250 0.5720 0.00698 0.00170 -0.0942 0.5562 0.9929
1.500 0.6000 0.00719 0.00176 -0.0943 0.5326 1.0000
1.750 0.6223 0.00736 0.00183 -0.0932 0.5122 1.0000
2.000 0.6452 0.00753 0.00192 -0.0922 0.4953 1.0000
2.250 0.6685 0.00769 0.00200 -0.0913 0.4800 1.0000
2.500 0.6921 0.00785 0.00210 -0.0905 0.4654 1.0000
2.750 0.7156 0.00803 0.00221 -0.0896 0.4499 1.0000
3.000 0.7395 0.00820 0.00233 -0.0888 0.4360 1.0000
3.250 0.7635 0.00838 0.00245 -0.0881 0.4225 1.0000
3.500 0.7870 0.00858 0.00260 -0.0873 0.4060 1.0000
3.750 0.8104 0.00881 0.00276 -0.0865 0.3887 1.0000
4.000 0.8345 0.00900 0.00292 -0.0858 0.3753 1.0000
4.250 0.8583 0.00921 0.00309 -0.0851 0.3601 1.0000
4.500 0.8811 0.00949 0.00330 -0.0842 0.3364 1.0000
4.750 0.9014 0.00995 0.00356 -0.0829 0.2959 1.0000
5.000 0.9195 0.01058 0.00390 -0.0813 0.2420 1.0000
5.250 0.9383 0.01120 0.00428 -0.0798 0.1952 1.0000
5.500 0.9550 0.01199 0.00476 -0.0781 0.1362 1.0000
5.750 0.9715 0.01279 0.00530 -0.0763 0.0905 1.0000
6.000 0.9926 0.01322 0.00568 -0.0752 0.0775 1.0000
6.250 1.0087 0.01404 0.00626 -0.0733 0.0308 1.0000
6.500 1.0280 0.01459 0.00681 -0.0719 0.0195 1.0000
6.750 1.0489 0.01501 0.00729 -0.0707 0.0161 1.0000
7.000 1.0694 0.01542 0.00776 -0.0695 0.0142 1.0000
7.250 1.0887 0.01592 0.00829 -0.0681 0.0123 1.0000
7.500 1.1064 0.01652 0.00897 -0.0664 0.0107 1.0000
7.750 1.1249 0.01701 0.00952 -0.0649 0.0101 1.0000
8.000 1.1415 0.01753 0.01011 -0.0630 0.0094 1.0000
8.250 1.1566 0.01812 0.01077 -0.0609 0.0088 1.0000
8.500 1.1713 0.01871 0.01141 -0.0588 0.0083 1.0000
8.750 1.1834 0.01946 0.01222 -0.0563 0.0077 1.0000
9.000 1.1938 0.02033 0.01316 -0.0537 0.0072 1.0000
9.250 1.2064 0.02106 0.01397 -0.0514 0.0068 1.0000
9.500 1.2176 0.02188 0.01487 -0.0491 0.0065 1.0000
9.750 1.2271 0.02282 0.01591 -0.0466 0.0062 1.0000
10.000 1.2363 0.02381 0.01697 -0.0442 0.0060 1.0000
10.250 1.2455 0.02482 0.01805 -0.0420 0.0058 1.0000
10.500 1.2528 0.02598 0.01929 -0.0397 0.0056 1.0000
10.750 1.2599 0.02720 0.02062 -0.0375 0.0054 1.0000
11.000 1.2651 0.02861 0.02210 -0.0353 0.0052 1.0000
11.250 1.2669 0.03036 0.02395 -0.0329 0.0051 1.0000
11.500 1.2668 0.03238 0.02607 -0.0306 0.0050 1.0000
11.750 1.2724 0.03400 0.02782 -0.0290 0.0048 1.0000
12.000 1.2770 0.03578 0.02971 -0.0275 0.0047 1.0000
12.250 1.2818 0.03760 0.03165 -0.0262 0.0045 1.0000
12.500 1.2845 0.03970 0.03388 -0.0249 0.0043 1.0000
12.750 1.2868 0.04193 0.03624 -0.0238 0.0042 1.0000
13.000 1.2878 0.04438 0.03882 -0.0229 0.0041 1.0000
13.250 1.2871 0.04715 0.04172 -0.0221 0.0040 1.0000
13.500 1.2883 0.04974 0.04443 -0.0217 0.0039 1.0000
13.750 1.2876 0.05266 0.04748 -0.0215 0.0038 1.0000
14.000 1.2852 0.05593 0.05089 -0.0214 0.0038 1.0000
14.250 1.2820 0.05942 0.05456 -0.0216 0.0038 1.0000
14.500 1.2818 0.06259 0.05781 -0.0223 0.0036 1.0000
14.750 1.2787 0.06629 0.06163 -0.0232 0.0035 1.0000
15.000 1.2722 0.07066 0.06616 -0.0241 0.0035 1.0000
15.250 1.2670 0.07499 0.07063 -0.0255 0.0035 1.0000
15.500 1.2599 0.07977 0.07555 -0.0271 0.0035 1.0000
15.750 1.2522 0.08480 0.08072 -0.0290 0.0034 1.0000
16.000 1.2432 0.09023 0.08629 -0.0313 0.0034 1.0000
16.250 1.2336 0.09596 0.09214 -0.0339 0.0034 1.0000
16.500 1.2218 0.10230 0.09867 -0.0368 0.0034 1.0000
16.750 1.2082 0.10916 0.10566 -0.0403 0.0033 1.0000
17.000 1.1960 0.11602 0.11269 -0.0439 0.0033 1.0000
17.250 1.1835 0.12321 0.12004 -0.0478 0.0033 1.0000
17.500 1.1681 0.13120 0.12817 -0.0523 0.0033 1.0000
17.750 1.1554 0.13896 0.13608 -0.0568 0.0033 1.0000
18.000 1.1409 0.14743 0.14471 -0.0619 0.0033 1.0000
18.250 1.1253 0.15657 0.15399 -0.0674 0.0033 1.0000
18.500 1.1068 0.16701 0.16460 -0.0737 0.0034 1.0000
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