GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 602 AIRFOIL (goe602-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.86 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe602-il-1000000-n5.txt Download as CSV file: xf-goe602-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4108 0.13023 0.12850 -0.0288 1.0000 0.0036
-12.250 -0.4099 0.12624 0.12452 -0.0298 1.0000 0.0037
-11.750 -0.7901 0.03177 0.02945 -0.0900 0.9891 0.0036
-11.500 -0.7757 0.02744 0.02476 -0.0932 0.9865 0.0037
-11.250 -0.7601 0.02487 0.02193 -0.0939 0.9820 0.0038
-11.000 -0.7375 0.02294 0.01978 -0.0950 0.9793 0.0039
-10.750 -0.7127 0.02113 0.01773 -0.0963 0.9775 0.0040
-10.500 -0.6888 0.01976 0.01618 -0.0968 0.9744 0.0042
-10.250 -0.6635 0.01877 0.01504 -0.0972 0.9707 0.0043
-10.000 -0.6358 0.01759 0.01366 -0.0982 0.9681 0.0044
-9.750 -0.6076 0.01629 0.01217 -0.0994 0.9660 0.0047
-9.500 -0.5828 0.01541 0.01118 -0.0994 0.9614 0.0049
-9.250 -0.5553 0.01466 0.01032 -0.0999 0.9573 0.0051
-9.000 -0.5256 0.01402 0.00957 -0.1008 0.9542 0.0054
-8.750 -0.4980 0.01338 0.00882 -0.1011 0.9500 0.0057
-8.500 -0.4712 0.01282 0.00816 -0.1012 0.9448 0.0060
-8.250 -0.4423 0.01229 0.00753 -0.1017 0.9403 0.0063
-8.000 -0.4150 0.01184 0.00698 -0.1019 0.9352 0.0065
-7.750 -0.3890 0.01126 0.00628 -0.1017 0.9294 0.0071
-7.250 -0.3352 0.01047 0.00536 -0.1016 0.9184 0.0083
-7.000 -0.3083 0.01016 0.00497 -0.1016 0.9127 0.0091
-6.750 -0.2817 0.00982 0.00458 -0.1014 0.9071 0.0103
-6.500 -0.2554 0.00955 0.00428 -0.1011 0.9007 0.0117
-6.250 -0.2283 0.00932 0.00401 -0.1010 0.8948 0.0132
-6.000 -0.2020 0.00911 0.00377 -0.1007 0.8880 0.0152
-5.500 -0.1479 0.00891 0.00354 -0.1004 0.8731 0.0193
-5.250 -0.1208 0.00886 0.00344 -0.1002 0.8651 0.0200
-5.000 -0.0947 0.00861 0.00312 -0.0999 0.8565 0.0213
-4.750 -0.0683 0.00842 0.00288 -0.0996 0.8485 0.0231
-4.500 -0.0418 0.00829 0.00271 -0.0993 0.8396 0.0244
-4.250 -0.0151 0.00816 0.00254 -0.0991 0.8303 0.0257
-4.000 0.0114 0.00804 0.00235 -0.0987 0.8202 0.0270
-3.750 0.0378 0.00794 0.00219 -0.0984 0.8091 0.0282
-3.500 0.0641 0.00784 0.00203 -0.0980 0.7968 0.0289
-3.250 0.0903 0.00778 0.00190 -0.0977 0.7829 0.0295
-3.000 0.1163 0.00772 0.00176 -0.0972 0.7684 0.0298
-2.750 0.1421 0.00760 0.00154 -0.0967 0.7540 0.0313
-2.500 0.1679 0.00754 0.00140 -0.0963 0.7389 0.0328
-2.250 0.1939 0.00750 0.00128 -0.0958 0.7239 0.0341
-1.750 0.2459 0.00746 0.00112 -0.0950 0.6945 0.0376
-1.500 0.2719 0.00745 0.00106 -0.0946 0.6796 0.0404
-1.250 0.2978 0.00742 0.00101 -0.0942 0.6651 0.0529
-1.000 0.3233 0.00730 0.00097 -0.0938 0.6505 0.0959
-0.750 0.3487 0.00720 0.00095 -0.0933 0.6350 0.1386
-0.500 0.3727 0.00692 0.00093 -0.0928 0.6180 0.2539
0.000 0.4212 0.00702 0.00098 -0.0914 0.5612 0.3240
0.250 0.4456 0.00709 0.00102 -0.0908 0.5331 0.3558
0.500 0.4699 0.00707 0.00106 -0.0902 0.5084 0.4164
0.750 0.4940 0.00698 0.00112 -0.0896 0.4892 0.5018
1.000 0.5181 0.00689 0.00120 -0.0889 0.4717 0.5863
1.250 0.5407 0.00668 0.00129 -0.0879 0.4578 0.7104
1.500 0.5584 0.00635 0.00142 -0.0856 0.4452 0.8709
1.750 0.5878 0.00636 0.00152 -0.0858 0.4302 0.9456
2.000 0.6277 0.00651 0.00161 -0.0886 0.4135 0.9704
2.250 0.6655 0.00667 0.00169 -0.0910 0.3981 0.9868
2.500 0.6991 0.00683 0.00179 -0.0924 0.3844 0.9995
2.750 0.7232 0.00699 0.00189 -0.0917 0.3686 1.0000
3.000 0.7471 0.00716 0.00199 -0.0909 0.3543 1.0000
3.250 0.7707 0.00735 0.00210 -0.0901 0.3361 1.0000
3.500 0.7939 0.00759 0.00225 -0.0893 0.3153 1.0000
3.750 0.8175 0.00780 0.00239 -0.0885 0.2967 1.0000
4.000 0.8384 0.00822 0.00260 -0.0873 0.2574 1.0000
4.250 0.8605 0.00857 0.00282 -0.0862 0.2282 1.0000
4.500 0.8800 0.00911 0.00312 -0.0848 0.1808 1.0000
4.750 0.8961 0.00994 0.00358 -0.0828 0.1087 1.0000
5.000 0.9179 0.01033 0.00386 -0.0818 0.0890 1.0000
5.250 0.9411 0.01062 0.00411 -0.0810 0.0792 1.0000
5.500 0.9645 0.01088 0.00436 -0.0803 0.0700 1.0000
5.750 0.9824 0.01157 0.00483 -0.0786 0.0266 1.0000
6.000 1.0046 0.01192 0.00517 -0.0776 0.0172 1.0000
6.250 1.0274 0.01222 0.00547 -0.0768 0.0144 1.0000
6.500 1.0494 0.01257 0.00582 -0.0758 0.0114 1.0000
6.750 1.0718 0.01287 0.00615 -0.0749 0.0103 1.0000
7.000 1.0939 0.01319 0.00649 -0.0740 0.0093 1.0000
7.250 1.1153 0.01355 0.00686 -0.0729 0.0084 1.0000
7.500 1.1352 0.01401 0.00734 -0.0716 0.0073 1.0000
7.750 1.1564 0.01434 0.00770 -0.0705 0.0069 1.0000
8.000 1.1769 0.01471 0.00812 -0.0693 0.0063 1.0000
8.250 1.1965 0.01512 0.00855 -0.0680 0.0059 1.0000
8.500 1.2150 0.01555 0.00901 -0.0665 0.0055 1.0000
8.750 1.2305 0.01607 0.00957 -0.0644 0.0052 1.0000
9.000 1.2452 0.01662 0.01017 -0.0622 0.0049 1.0000
9.250 1.2608 0.01711 0.01071 -0.0602 0.0047 1.0000
9.500 1.2761 0.01761 0.01127 -0.0582 0.0045 1.0000
9.750 1.2906 0.01817 0.01187 -0.0562 0.0043 1.0000
10.000 1.3038 0.01880 0.01259 -0.0540 0.0041 1.0000
10.250 1.3188 0.01933 0.01315 -0.0521 0.0038 1.0000
10.500 1.3321 0.01997 0.01383 -0.0501 0.0037 1.0000
10.750 1.3439 0.02070 0.01461 -0.0480 0.0035 1.0000
11.000 1.3501 0.02179 0.01578 -0.0451 0.0033 1.0000
11.250 1.3590 0.02274 0.01681 -0.0428 0.0032 1.0000
11.500 1.3687 0.02367 0.01781 -0.0407 0.0032 1.0000
11.750 1.3777 0.02467 0.01890 -0.0386 0.0031 1.0000
12.000 1.3841 0.02588 0.02020 -0.0364 0.0030 1.0000
12.250 1.3910 0.02711 0.02151 -0.0344 0.0030 1.0000
12.500 1.3964 0.02850 0.02299 -0.0324 0.0029 1.0000
12.750 1.4008 0.03003 0.02462 -0.0305 0.0028 1.0000
13.000 1.4045 0.03168 0.02639 -0.0288 0.0027 1.0000
13.250 1.4049 0.03372 0.02853 -0.0270 0.0027 1.0000
13.500 1.4104 0.03538 0.03028 -0.0259 0.0026 1.0000
13.750 1.4129 0.03741 0.03240 -0.0248 0.0026 1.0000
14.000 1.4107 0.04001 0.03512 -0.0237 0.0026 1.0000
14.250 1.4091 0.04269 0.03792 -0.0230 0.0025 1.0000
14.500 1.4157 0.04459 0.03987 -0.0227 0.0024 1.0000
14.750 1.4177 0.04707 0.04244 -0.0224 0.0023 1.0000
15.000 1.4100 0.05085 0.04636 -0.0224 0.0023 1.0000
15.250 1.4085 0.05403 0.04964 -0.0227 0.0023 1.0000
15.500 1.4040 0.05773 0.05346 -0.0232 0.0023 1.0000
15.750 1.3993 0.06162 0.05746 -0.0240 0.0022 1.0000
16.000 1.3942 0.06573 0.06167 -0.0250 0.0022 1.0000
16.250 1.3890 0.06999 0.06602 -0.0263 0.0021 1.0000
16.500 1.3775 0.07530 0.07148 -0.0280 0.0022 1.0000
16.750 1.3684 0.08049 0.07677 -0.0300 0.0021 1.0000
17.000 1.3580 0.08602 0.08243 -0.0321 0.0021 1.0000
17.250 1.3458 0.09197 0.08852 -0.0345 0.0021 1.0000
17.500 1.3304 0.09873 0.09541 -0.0376 0.0020 1.0000
17.750 1.3201 0.10472 0.10153 -0.0404 0.0021 1.0000
18.000 1.3080 0.11116 0.10809 -0.0435 0.0021 1.0000
18.250 1.2928 0.11839 0.11545 -0.0471 0.0021 1.0000
18.500 1.2787 0.12559 0.12278 -0.0509 0.0020 1.0000
18.750 1.2649 0.13290 0.13021 -0.0548 0.0020 1.0000
19.000 1.2545 0.13958 0.13700 -0.0585 0.0020 1.0000
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Polar data table (+)
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