GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 500,000 Max Cl/Cd: 100.08 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe335-il-500000-n5.txt Download as CSV file: xf-goe335-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 335 (D.F.W.) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3275 0.10568 0.10343 -0.0229 1.0000 0.0069
-9.000 -0.3231 0.10319 0.10095 -0.0231 1.0000 0.0066
-8.750 -0.3202 0.10025 0.09804 -0.0235 1.0000 0.0066
-8.500 -0.3171 0.09767 0.09549 -0.0237 1.0000 0.0062
-8.250 -0.3168 0.09453 0.09238 -0.0240 1.0000 0.0065
-8.000 -0.3157 0.09211 0.09000 -0.0239 1.0000 0.0064
-7.500 -0.2994 0.08655 0.08447 -0.0276 0.9963 0.0084
-7.000 -0.2646 0.07531 0.07325 -0.0417 0.9769 0.0070
-6.750 -0.2412 0.07027 0.06817 -0.0491 0.9652 0.0069
-6.250 -0.1783 0.05828 0.05607 -0.0684 0.9338 0.0070
-6.000 -0.1377 0.05080 0.04842 -0.0804 0.8998 0.0072
-5.750 -0.1058 0.04663 0.04399 -0.0866 0.8584 0.0076
-5.500 -0.0824 0.04330 0.04044 -0.0896 0.8334 0.0081
-5.000 -0.0422 0.01363 0.00842 -0.1001 0.8100 0.0114
-4.750 -0.0154 0.01377 0.00850 -0.0997 0.7983 0.0125
-4.500 0.0111 0.01355 0.00814 -0.0994 0.7878 0.0140
-4.250 0.0373 0.01279 0.00712 -0.0990 0.7787 0.0160
-4.000 0.0641 0.01302 0.00734 -0.0988 0.7686 0.0174
-3.750 0.0910 0.01317 0.00743 -0.0985 0.7578 0.0188
-3.500 0.1177 0.01304 0.00719 -0.0982 0.7466 0.0214
-3.250 0.1443 0.01276 0.00674 -0.0979 0.7359 0.0237
-3.000 0.1711 0.01263 0.00647 -0.0975 0.7259 0.0250
-2.750 0.1976 0.01207 0.00573 -0.0972 0.7155 0.0264
-2.500 0.2236 0.01129 0.00479 -0.0969 0.7044 0.0284
-2.250 0.2501 0.01107 0.00448 -0.0966 0.6921 0.0302
-2.000 0.2765 0.01077 0.00406 -0.0962 0.6797 0.0315
-1.750 0.3029 0.01046 0.00362 -0.0958 0.6670 0.0323
-1.500 0.3292 0.01018 0.00323 -0.0954 0.6532 0.0329
-1.250 0.3554 0.00993 0.00287 -0.0949 0.6383 0.0332
-1.000 0.3815 0.00977 0.00260 -0.0945 0.6211 0.0340
-0.750 0.4073 0.00962 0.00234 -0.0940 0.6009 0.0344
-0.500 0.4329 0.00950 0.00210 -0.0935 0.5769 0.0343
-0.250 0.4582 0.00945 0.00189 -0.0929 0.5469 0.0343
0.250 0.5080 0.00957 0.00165 -0.0917 0.4751 0.0345
0.500 0.5333 0.00966 0.00159 -0.0912 0.4496 0.0348
0.750 0.5592 0.00974 0.00156 -0.0908 0.4314 0.0354
1.000 0.5853 0.00981 0.00154 -0.0904 0.4177 0.0367
1.250 0.6114 0.00988 0.00155 -0.0900 0.4063 0.0392
1.750 0.6635 0.00983 0.00171 -0.0894 0.3862 0.1473
2.000 0.6888 0.00966 0.00186 -0.0891 0.3771 0.3060
2.500 0.7474 0.00850 0.00213 -0.0902 0.3621 1.0000
2.750 0.7735 0.00863 0.00223 -0.0898 0.3565 1.0000
3.000 0.7994 0.00879 0.00234 -0.0894 0.3513 1.0000
3.250 0.8256 0.00891 0.00245 -0.0891 0.3458 1.0000
3.500 0.8513 0.00908 0.00258 -0.0887 0.3382 1.0000
3.750 0.8772 0.00923 0.00272 -0.0883 0.3307 1.0000
4.000 0.9029 0.00940 0.00286 -0.0880 0.3241 1.0000
4.250 0.9287 0.00956 0.00302 -0.0876 0.3187 1.0000
4.500 0.9547 0.00970 0.00319 -0.0873 0.3134 1.0000
4.750 0.9802 0.00988 0.00337 -0.0869 0.3082 1.0000
5.000 1.0058 0.01005 0.00355 -0.0865 0.2981 1.0000
5.250 1.0302 0.01032 0.00373 -0.0860 0.2777 1.0000
5.500 1.0547 0.01060 0.00394 -0.0855 0.2540 1.0000
5.750 1.0766 0.01113 0.00424 -0.0846 0.2084 1.0000
6.000 1.0936 0.01221 0.00491 -0.0831 0.1383 1.0000
6.250 1.1091 0.01349 0.00578 -0.0814 0.0622 1.0000
6.500 1.1270 0.01451 0.00656 -0.0799 0.0162 1.0000
6.750 1.1501 0.01493 0.00705 -0.0791 0.0127 1.0000
7.000 1.1723 0.01541 0.00763 -0.0782 0.0109 1.0000
7.250 1.1930 0.01606 0.00837 -0.0771 0.0091 1.0000
7.500 1.2141 0.01663 0.00903 -0.0761 0.0081 1.0000
7.750 1.2349 0.01720 0.00968 -0.0750 0.0073 1.0000
8.000 1.2545 0.01785 0.01043 -0.0738 0.0067 1.0000
8.250 1.2729 0.01858 0.01124 -0.0724 0.0062 1.0000
8.500 1.2877 0.01959 0.01234 -0.0705 0.0058 1.0000
8.750 1.3010 0.02066 0.01353 -0.0684 0.0055 1.0000
9.000 1.3164 0.02146 0.01442 -0.0666 0.0052 1.0000
9.250 1.3309 0.02227 0.01532 -0.0648 0.0047 1.0000
9.500 1.3427 0.02312 0.01625 -0.0625 0.0044 1.0000
9.750 1.3506 0.02410 0.01731 -0.0596 0.0042 1.0000
10.000 1.3569 0.02517 0.01847 -0.0567 0.0041 1.0000
10.250 1.3617 0.02638 0.01980 -0.0538 0.0039 1.0000
10.500 1.3640 0.02783 0.02135 -0.0509 0.0038 1.0000
10.750 1.3603 0.02985 0.02348 -0.0478 0.0037 1.0000
11.000 1.3594 0.03185 0.02560 -0.0453 0.0036 1.0000
11.250 1.3612 0.03379 0.02767 -0.0435 0.0035 1.0000
11.500 1.3623 0.03596 0.02999 -0.0419 0.0034 1.0000
11.750 1.3620 0.03842 0.03259 -0.0405 0.0034 1.0000
12.000 1.3618 0.04102 0.03534 -0.0393 0.0033 1.0000
12.250 1.3608 0.04381 0.03828 -0.0383 0.0032 1.0000
12.500 1.3593 0.04684 0.04148 -0.0375 0.0031 1.0000
12.750 1.3567 0.05010 0.04491 -0.0369 0.0030 1.0000
13.000 1.3536 0.05355 0.04852 -0.0366 0.0030 1.0000
13.250 1.3493 0.05727 0.05243 -0.0366 0.0030 1.0000
13.500 1.3448 0.06111 0.05643 -0.0370 0.0029 1.0000
13.750 1.3374 0.06558 0.06109 -0.0376 0.0028 1.0000
14.000 1.3299 0.07016 0.06585 -0.0387 0.0028 1.0000
14.250 1.3211 0.07518 0.07105 -0.0402 0.0028 1.0000
14.500 1.3134 0.08020 0.07622 -0.0422 0.0027 1.0000
14.750 1.3071 0.08513 0.08128 -0.0445 0.0026 1.0000
15.000 1.2949 0.09147 0.08780 -0.0473 0.0026 1.0000
15.250 1.2870 0.09717 0.09364 -0.0502 0.0026 1.0000
15.500 1.2773 0.10339 0.10000 -0.0534 0.0025 1.0000
15.750 1.2690 0.10947 0.10619 -0.0568 0.0025 1.0000
16.000 1.2536 0.11729 0.11420 -0.0609 0.0025 1.0000
16.250 1.2415 0.12463 0.12168 -0.0650 0.0025 1.0000
16.500 1.2302 0.13195 0.12913 -0.0692 0.0025 1.0000
16.750 1.2197 0.13932 0.13662 -0.0736 0.0024 1.0000
17.000 1.2008 0.14929 0.14677 -0.0795 0.0025 1.0000
17.250 1.1877 0.15813 0.15574 -0.0849 0.0025 1.0000
17.500 1.1660 0.17033 0.16811 -0.0922 0.0025 1.0000
17.750 1.1243 0.19217 0.19016 -0.1044 0.0028 1.0000
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Polar data table (+)
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