GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 50,000 Max Cl/Cd: 33.1 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe599-il-50000-n5.txt Download as CSV file: xf-goe599-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5596 0.09562 0.08842 -0.0307 1.0000 0.0496
-9.750 -0.5674 0.08954 0.08242 -0.0342 1.0000 0.0493
-9.500 -0.5792 0.08225 0.07520 -0.0390 1.0000 0.0486
-9.250 -0.5992 0.07505 0.06804 -0.0442 1.0000 0.0473
-9.000 -0.6226 0.06917 0.06211 -0.0464 1.0000 0.0462
-8.750 -0.6389 0.06404 0.05682 -0.0472 1.0000 0.0459
-8.500 -0.6475 0.05975 0.05233 -0.0469 1.0000 0.0464
-8.250 -0.6513 0.05579 0.04811 -0.0461 1.0000 0.0474
-8.000 -0.6517 0.05189 0.04388 -0.0451 1.0000 0.0486
-7.750 -0.6484 0.04802 0.03958 -0.0438 1.0000 0.0498
-7.500 -0.6410 0.04423 0.03529 -0.0424 1.0000 0.0510
-7.250 -0.6295 0.04073 0.03123 -0.0410 1.0000 0.0524
-7.000 -0.6151 0.03779 0.02777 -0.0396 1.0000 0.0554
-6.750 -0.5983 0.03595 0.02584 -0.0385 1.0000 0.0594
-6.500 -0.5795 0.03373 0.02327 -0.0372 1.0000 0.0631
-6.250 -0.5593 0.03169 0.02086 -0.0359 1.0000 0.0681
-6.000 -0.5399 0.03039 0.01951 -0.0348 1.0000 0.0750
-5.750 -0.5185 0.02880 0.01768 -0.0334 1.0000 0.0812
-5.500 -0.4977 0.02769 0.01636 -0.0323 1.0000 0.0921
-5.250 -0.4773 0.02637 0.01498 -0.0311 1.0000 0.1031
-5.000 -0.4565 0.02501 0.01357 -0.0299 1.0000 0.1162
-4.750 -0.4359 0.02368 0.01236 -0.0290 1.0000 0.1412
-4.500 -0.4142 0.02249 0.01143 -0.0285 1.0000 0.1844
-4.250 -0.3930 0.02156 0.01072 -0.0278 1.0000 0.2457
-4.000 -0.3731 0.02074 0.01027 -0.0269 1.0000 0.3347
-3.750 -0.3541 0.02008 0.01006 -0.0255 1.0000 0.4293
-3.500 -0.3340 0.01967 0.00984 -0.0239 1.0000 0.4958
-3.250 -0.3131 0.01938 0.00959 -0.0225 1.0000 0.5507
-3.000 -0.2927 0.01913 0.00937 -0.0208 1.0000 0.6067
-2.750 -0.2735 0.01890 0.00927 -0.0187 1.0000 0.6672
-2.500 -0.2550 0.01871 0.00923 -0.0162 1.0000 0.7292
-2.250 -0.2358 0.01859 0.00923 -0.0136 1.0000 0.7963
-2.000 -0.2081 0.01857 0.00920 -0.0127 1.0000 0.8736
-1.750 -0.1598 0.01862 0.00910 -0.0168 1.0000 0.9608
-1.500 -0.1302 0.01860 0.00883 -0.0185 1.0000 1.0000
-1.250 -0.1141 0.01866 0.00868 -0.0175 1.0000 1.0000
-1.000 -0.0961 0.01880 0.00862 -0.0167 1.0000 1.0000
-0.750 -0.0770 0.01899 0.00864 -0.0161 1.0000 1.0000
-0.500 -0.0454 0.01927 0.00874 -0.0179 0.9955 1.0000
-0.250 -0.0057 0.01960 0.00891 -0.0211 0.9873 1.0000
0.000 0.0336 0.01991 0.00910 -0.0242 0.9784 1.0000
0.250 0.0725 0.02021 0.00930 -0.0272 0.9686 1.0000
0.500 0.1116 0.02048 0.00951 -0.0301 0.9581 1.0000
0.750 0.1518 0.02072 0.00971 -0.0330 0.9470 1.0000
1.000 0.1935 0.02092 0.00990 -0.0362 0.9358 1.0000
1.250 0.2303 0.02106 0.01006 -0.0383 0.9225 1.0000
1.500 0.2667 0.02118 0.01022 -0.0402 0.9091 1.0000
1.750 0.3030 0.02128 0.01038 -0.0420 0.8959 1.0000
2.000 0.3397 0.02136 0.01055 -0.0438 0.8829 1.0000
2.250 0.3762 0.02141 0.01071 -0.0454 0.8700 1.0000
2.500 0.4113 0.02145 0.01089 -0.0466 0.8568 1.0000
2.750 0.4457 0.02148 0.01105 -0.0477 0.8433 1.0000
3.000 0.4796 0.02149 0.01123 -0.0485 0.8289 1.0000
3.250 0.5165 0.02124 0.01116 -0.0492 0.8099 1.0000
3.500 0.5487 0.02098 0.01105 -0.0488 0.7845 1.0000
3.750 0.5788 0.02070 0.01092 -0.0478 0.7545 1.0000
4.000 0.6061 0.02039 0.01070 -0.0461 0.7161 1.0000
4.250 0.6293 0.02017 0.01048 -0.0437 0.6634 1.0000
4.500 0.6521 0.02009 0.01024 -0.0412 0.5948 1.0000
4.750 0.6739 0.02036 0.01031 -0.0390 0.5211 1.0000
5.000 0.6912 0.02106 0.01056 -0.0363 0.4255 1.0000
5.250 0.7025 0.02242 0.01120 -0.0334 0.2845 1.0000
5.500 0.7117 0.02453 0.01230 -0.0312 0.1691 1.0000
5.750 0.7285 0.02603 0.01363 -0.0297 0.1430 1.0000
6.000 0.7471 0.02727 0.01490 -0.0284 0.1310 1.0000
6.250 0.7668 0.02844 0.01615 -0.0272 0.1228 1.0000
6.500 0.7882 0.02962 0.01745 -0.0261 0.1170 1.0000
6.750 0.8113 0.03079 0.01877 -0.0252 0.1103 1.0000
7.000 0.8347 0.03207 0.02017 -0.0246 0.1031 1.0000
7.250 0.8614 0.03346 0.02175 -0.0241 0.0976 1.0000
7.500 0.8899 0.03529 0.02355 -0.0241 0.0929 1.0000
7.750 0.9138 0.03691 0.02554 -0.0234 0.0851 1.0000
8.000 0.9374 0.03900 0.02768 -0.0230 0.0784 1.0000
8.250 0.9568 0.04102 0.03007 -0.0219 0.0708 1.0000
8.500 0.9770 0.04384 0.03303 -0.0212 0.0655 1.0000
8.750 0.9901 0.04655 0.03640 -0.0192 0.0599 1.0000
9.000 1.0040 0.04949 0.03964 -0.0178 0.0561 1.0000
9.250 1.0165 0.05328 0.04345 -0.0169 0.0530 1.0000
9.500 1.0154 0.05643 0.04734 -0.0137 0.0507 1.0000
9.750 1.0118 0.06000 0.05143 -0.0110 0.0486 1.0000
10.000 1.0051 0.06371 0.05555 -0.0084 0.0473 1.0000
10.250 0.9942 0.06757 0.05974 -0.0060 0.0467 1.0000
10.500 0.9774 0.07131 0.06375 -0.0034 0.0464 1.0000
10.750 0.9576 0.07546 0.06812 -0.0018 0.0464 1.0000
11.000 0.9352 0.08027 0.07313 -0.0018 0.0465 1.0000
11.250 0.9110 0.08603 0.07905 -0.0035 0.0469 1.0000
11.500 0.8860 0.09297 0.08611 -0.0072 0.0475 1.0000
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