GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.2 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe534-il-1000000-n5.txt Download as CSV file: xf-goe534-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 534 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7596 0.08875 0.08600 -0.0480 1.0000 0.0235
-15.500 -0.7758 0.08259 0.07977 -0.0519 1.0000 0.0237
-15.250 -0.7933 0.07640 0.07351 -0.0559 1.0000 0.0238
-15.000 -0.8150 0.06977 0.06679 -0.0603 1.0000 0.0239
-14.750 -0.8418 0.06280 0.05974 -0.0650 1.0000 0.0240
-14.500 -0.8804 0.05493 0.05177 -0.0706 1.0000 0.0239
-14.250 -0.9428 0.04611 0.04284 -0.0755 1.0000 0.0239
-14.000 -0.9988 0.03505 0.03157 -0.0854 1.0000 0.0238
-13.750 -1.0011 0.02895 0.02527 -0.0915 1.0000 0.0239
-13.500 -0.9795 0.02503 0.02116 -0.0969 0.9992 0.0241
-13.250 -0.9484 0.02326 0.01927 -0.1000 0.9971 0.0243
-13.000 -0.9161 0.02194 0.01786 -0.1025 0.9938 0.0244
-12.750 -0.8866 0.02063 0.01646 -0.1044 0.9889 0.0247
-12.500 -0.8562 0.01937 0.01513 -0.1062 0.9830 0.0250
-12.250 -0.8268 0.01843 0.01412 -0.1073 0.9760 0.0253
-11.750 -0.7528 0.01679 0.01235 -0.1119 0.9565 0.0259
-11.500 -0.7059 0.01603 0.01149 -0.1160 0.9298 0.0262
-11.250 -0.6743 0.01557 0.01080 -0.1167 0.8757 0.0265
-11.000 -0.6513 0.01523 0.01026 -0.1157 0.8369 0.0268
-10.750 -0.6275 0.01488 0.00976 -0.1148 0.8109 0.0271
-10.500 -0.6027 0.01454 0.00930 -0.1141 0.7927 0.0274
-10.250 -0.5776 0.01420 0.00885 -0.1134 0.7776 0.0276
-10.000 -0.5520 0.01388 0.00843 -0.1128 0.7641 0.0278
-9.750 -0.5260 0.01354 0.00802 -0.1122 0.7537 0.0280
-9.500 -0.5005 0.01311 0.00750 -0.1116 0.7434 0.0284
-9.250 -0.4744 0.01273 0.00706 -0.1110 0.7341 0.0288
-9.000 -0.4480 0.01241 0.00667 -0.1105 0.7244 0.0292
-8.750 -0.4214 0.01210 0.00630 -0.1099 0.7165 0.0296
-8.500 -0.3944 0.01182 0.00596 -0.1094 0.7082 0.0300
-8.250 -0.3676 0.01158 0.00566 -0.1089 0.6986 0.0304
-8.000 -0.3402 0.01134 0.00536 -0.1084 0.6902 0.0309
-7.750 -0.3129 0.01113 0.00509 -0.1079 0.6808 0.0314
-7.500 -0.2855 0.01091 0.00482 -0.1074 0.6717 0.0320
-7.250 -0.2584 0.01067 0.00452 -0.1069 0.6597 0.0329
-7.000 -0.2310 0.01046 0.00426 -0.1064 0.6472 0.0337
-6.750 -0.2037 0.01029 0.00402 -0.1059 0.6339 0.0347
-6.500 -0.1764 0.01014 0.00380 -0.1053 0.6168 0.0359
-6.250 -0.1495 0.00997 0.00355 -0.1047 0.5955 0.0385
-5.750 -0.0956 0.00971 0.00326 -0.1037 0.5546 0.0586
-5.500 -0.0679 0.00971 0.00320 -0.1032 0.5379 0.0626
-5.000 -0.0119 0.00969 0.00305 -0.1022 0.5117 0.0666
-4.750 0.0160 0.00967 0.00300 -0.1018 0.5007 0.0686
-4.500 0.0442 0.00964 0.00294 -0.1014 0.4907 0.0700
-4.250 0.0722 0.00963 0.00287 -0.1010 0.4810 0.0712
-4.000 0.1003 0.00962 0.00280 -0.1005 0.4695 0.0721
-3.750 0.1284 0.00963 0.00275 -0.1001 0.4581 0.0729
-3.500 0.1564 0.00961 0.00267 -0.0997 0.4481 0.0736
-3.250 0.1843 0.00954 0.00257 -0.0993 0.4407 0.0746
-3.000 0.2125 0.00948 0.00249 -0.0989 0.4330 0.0755
-2.750 0.2404 0.00947 0.00244 -0.0985 0.4250 0.0765
-2.500 0.2687 0.00944 0.00239 -0.0981 0.4193 0.0777
-2.250 0.2969 0.00942 0.00234 -0.0977 0.4124 0.0787
-2.000 0.3248 0.00943 0.00230 -0.0973 0.4045 0.0794
-1.750 0.3531 0.00941 0.00226 -0.0970 0.3981 0.0801
-1.500 0.3811 0.00941 0.00223 -0.0966 0.3907 0.0808
-1.250 0.4091 0.00942 0.00221 -0.0962 0.3845 0.0818
-1.000 0.4372 0.00938 0.00216 -0.0958 0.3786 0.0834
-0.750 0.4651 0.00939 0.00214 -0.0954 0.3712 0.0845
-0.500 0.4929 0.00940 0.00213 -0.0950 0.3642 0.0854
-0.250 0.5208 0.00942 0.00212 -0.0946 0.3561 0.0865
0.000 0.5484 0.00946 0.00213 -0.0942 0.3487 0.0876
0.250 0.5764 0.00948 0.00214 -0.0938 0.3423 0.0889
0.500 0.6040 0.00954 0.00216 -0.0934 0.3342 0.0901
0.750 0.6316 0.00958 0.00218 -0.0930 0.3264 0.0931
1.000 0.6588 0.00965 0.00222 -0.0925 0.3168 0.0972
1.250 0.6862 0.00967 0.00226 -0.0921 0.3095 0.1074
1.500 0.7129 0.00960 0.00230 -0.0916 0.3013 0.1591
1.750 0.7396 0.00958 0.00237 -0.0912 0.2934 0.2037
2.000 0.7664 0.00963 0.00246 -0.0907 0.2839 0.2323
2.250 0.7931 0.00970 0.00256 -0.0902 0.2758 0.2563
2.500 0.8198 0.00977 0.00267 -0.0897 0.2678 0.2818
2.750 0.8464 0.00989 0.00278 -0.0892 0.2601 0.2994
3.250 0.8993 0.01014 0.00303 -0.0881 0.2449 0.3304
3.500 0.9259 0.01025 0.00316 -0.0877 0.2387 0.3459
3.750 0.9519 0.01041 0.00331 -0.0871 0.2314 0.3617
4.000 0.9784 0.01054 0.00345 -0.0866 0.2263 0.3749
4.250 1.0048 0.01065 0.00359 -0.0860 0.2217 0.3892
4.500 1.0307 0.01081 0.00375 -0.0855 0.2166 0.4038
4.750 1.0566 0.01097 0.00392 -0.0849 0.2119 0.4164
5.000 1.0828 0.01109 0.00407 -0.0844 0.2084 0.4305
5.250 1.1086 0.01124 0.00423 -0.0838 0.2048 0.4426
5.500 1.1341 0.01141 0.00441 -0.0832 0.2008 0.4571
5.750 1.1592 0.01159 0.00461 -0.0825 0.1966 0.4733
6.000 1.1849 0.01171 0.00478 -0.0819 0.1938 0.4900
6.250 1.2102 0.01186 0.00496 -0.0813 0.1906 0.5050
6.500 1.2349 0.01204 0.00516 -0.0806 0.1870 0.5198
6.750 1.2590 0.01224 0.00539 -0.0798 0.1827 0.5386
7.250 1.3068 0.01242 0.00582 -0.0782 0.1770 0.6488
7.750 1.3753 0.01248 0.00643 -0.0811 0.1671 1.0000
8.000 1.3992 0.01271 0.00665 -0.0803 0.1633 1.0000
8.250 1.4219 0.01301 0.00691 -0.0794 0.1581 1.0000
8.500 1.4441 0.01332 0.00720 -0.0784 0.1538 1.0000
8.750 1.4671 0.01357 0.00745 -0.0775 0.1507 1.0000
9.000 1.4891 0.01386 0.00773 -0.0764 0.1470 1.0000
9.250 1.5099 0.01421 0.00805 -0.0752 0.1429 1.0000
9.500 1.5310 0.01452 0.00836 -0.0741 0.1393 1.0000
9.750 1.5515 0.01484 0.00868 -0.0728 0.1359 1.0000
10.000 1.5704 0.01523 0.00905 -0.0714 0.1317 1.0000
10.250 1.5880 0.01560 0.00942 -0.0696 0.1285 1.0000
10.500 1.6048 0.01593 0.00977 -0.0678 0.1259 1.0000
10.750 1.6202 0.01632 0.01016 -0.0657 0.1229 1.0000
11.000 1.6346 0.01678 0.01061 -0.0636 0.1197 1.0000
11.250 1.6494 0.01724 0.01109 -0.0617 0.1170 1.0000
11.500 1.6646 0.01770 0.01157 -0.0599 0.1145 1.0000
11.750 1.6788 0.01823 0.01211 -0.0580 0.1119 1.0000
12.000 1.6916 0.01886 0.01274 -0.0561 0.1091 1.0000
12.250 1.7040 0.01954 0.01344 -0.0543 0.1063 1.0000
12.500 1.7178 0.02019 0.01412 -0.0527 0.1044 1.0000
12.750 1.7301 0.02095 0.01491 -0.0512 0.1021 1.0000
13.000 1.7412 0.02184 0.01583 -0.0497 0.0999 1.0000
13.250 1.7509 0.02290 0.01691 -0.0482 0.0975 1.0000
13.500 1.7623 0.02390 0.01796 -0.0470 0.0958 1.0000
13.750 1.7734 0.02499 0.01909 -0.0460 0.0942 1.0000
14.000 1.7821 0.02633 0.02046 -0.0450 0.0916 1.0000
14.250 1.7891 0.02788 0.02204 -0.0441 0.0893 1.0000
14.500 1.7952 0.02956 0.02376 -0.0433 0.0868 1.0000
14.750 1.8024 0.03121 0.02546 -0.0426 0.0848 1.0000
15.000 1.8066 0.03318 0.02747 -0.0420 0.0823 1.0000
15.250 1.8072 0.03553 0.02985 -0.0415 0.0796 1.0000
15.500 1.8099 0.03774 0.03212 -0.0411 0.0780 1.0000
15.750 1.8116 0.04009 0.03454 -0.0407 0.0763 1.0000
16.000 1.8115 0.04267 0.03718 -0.0405 0.0749 1.0000
16.250 1.8085 0.04563 0.04020 -0.0404 0.0734 1.0000
16.500 1.8035 0.04893 0.04357 -0.0405 0.0720 1.0000
16.750 1.7977 0.05241 0.04712 -0.0408 0.0705 1.0000
17.000 1.7932 0.05582 0.05061 -0.0411 0.0695 1.0000
17.250 1.7867 0.05953 0.05440 -0.0416 0.0683 1.0000
17.500 1.7771 0.06365 0.05860 -0.0422 0.0669 1.0000
17.750 1.7651 0.06812 0.06315 -0.0430 0.0656 1.0000
18.000 1.7523 0.07276 0.06787 -0.0439 0.0646 1.0000
18.250 1.7388 0.07750 0.07270 -0.0448 0.0638 1.0000
18.500 1.7272 0.08207 0.07736 -0.0458 0.0628 1.0000
18.750 1.7156 0.08672 0.08210 -0.0470 0.0622 1.0000
19.000 1.7022 0.09161 0.08708 -0.0482 0.0610 1.0000
19.250 1.6892 0.09658 0.09212 -0.0496 0.0602 1.0000
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Polar data table (+)
Polar graphs
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