WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 77-080 (fx77080-il) Reynolds number: 200,000 Max Cl/Cd: 43.2 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx77080-il-200000-n5.txt Download as CSV file: xf-fx77080-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 77-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.8287 0.08978 0.08595 -0.0023 1.0000 0.0157
-12.250 -0.8642 0.07644 0.07255 -0.0113 1.0000 0.0155
-12.000 -0.8927 0.06474 0.06069 -0.0214 1.0000 0.0153
-11.750 -0.9129 0.05700 0.05276 -0.0283 1.0000 0.0152
-11.500 -0.9363 0.05092 0.04644 -0.0319 1.0000 0.0150
-11.250 -0.9535 0.04698 0.04225 -0.0319 1.0000 0.0152
-11.000 -0.9682 0.04382 0.03882 -0.0296 1.0000 0.0152
-10.750 -0.9749 0.04090 0.03560 -0.0274 1.0000 0.0154
-10.500 -0.9767 0.03796 0.03230 -0.0252 1.0000 0.0155
-10.250 -0.9735 0.03527 0.02928 -0.0231 1.0000 0.0158
-10.000 -0.9662 0.03291 0.02672 -0.0213 1.0000 0.0162
-9.750 -0.9544 0.03112 0.02472 -0.0198 1.0000 0.0166
-9.500 -0.9403 0.02959 0.02303 -0.0183 1.0000 0.0172
-9.250 -0.9249 0.02813 0.02138 -0.0168 1.0000 0.0178
-9.000 -0.9085 0.02671 0.01976 -0.0154 1.0000 0.0186
-8.750 -0.8908 0.02543 0.01827 -0.0140 1.0000 0.0197
-8.500 -0.8723 0.02420 0.01682 -0.0126 1.0000 0.0206
-8.250 -0.8545 0.02289 0.01535 -0.0112 1.0000 0.0218
-8.000 -0.8355 0.02193 0.01434 -0.0100 1.0000 0.0233
-7.750 -0.8158 0.02098 0.01329 -0.0087 1.0000 0.0246
-7.500 -0.7957 0.02006 0.01225 -0.0074 1.0000 0.0261
-7.250 -0.7745 0.01933 0.01137 -0.0062 1.0000 0.0280
-7.000 -0.7557 0.01833 0.01035 -0.0048 1.0000 0.0304
-6.750 -0.7348 0.01762 0.00955 -0.0036 1.0000 0.0330
-6.500 -0.7136 0.01696 0.00878 -0.0023 1.0000 0.0356
-6.250 -0.6929 0.01624 0.00803 -0.0010 1.0000 0.0395
-6.000 -0.6713 0.01567 0.00742 0.0001 1.0000 0.0443
-5.750 -0.6498 0.01509 0.00679 0.0013 1.0000 0.0496
-5.500 -0.6281 0.01456 0.00624 0.0025 1.0000 0.0581
-5.250 -0.6065 0.01404 0.00577 0.0037 1.0000 0.0703
-5.000 -0.5846 0.01359 0.00538 0.0048 1.0000 0.0861
-4.750 -0.5625 0.01319 0.00506 0.0059 1.0000 0.1043
-4.500 -0.5401 0.01287 0.00475 0.0070 1.0000 0.1206
-4.250 -0.5177 0.01257 0.00446 0.0081 1.0000 0.1357
-4.000 -0.4955 0.01228 0.00420 0.0092 1.0000 0.1513
-3.750 -0.4733 0.01200 0.00396 0.0103 1.0000 0.1678
-3.500 -0.4515 0.01169 0.00373 0.0114 1.0000 0.1878
-3.250 -0.4299 0.01139 0.00353 0.0126 1.0000 0.2121
-3.000 -0.4085 0.01109 0.00334 0.0139 1.0000 0.2395
-2.500 -0.3668 0.01048 0.00304 0.0165 1.0000 0.3144
-2.250 -0.3465 0.01018 0.00294 0.0179 1.0000 0.3634
-2.000 -0.3233 0.00987 0.00286 0.0187 0.9988 0.4190
-1.750 -0.2869 0.00949 0.00278 0.0167 0.9912 0.4923
-1.500 -0.2529 0.00911 0.00273 0.0153 0.9839 0.5726
-1.250 -0.2208 0.00877 0.00272 0.0146 0.9760 0.6486
-1.000 -0.1876 0.00846 0.00273 0.0139 0.9676 0.7252
-0.750 -0.1483 0.00825 0.00276 0.0120 0.9604 0.7930
-0.500 -0.1072 0.00815 0.00280 0.0098 0.9505 0.8458
-0.250 -0.0577 0.00811 0.00283 0.0057 0.9388 0.8872
0.000 0.0003 0.00809 0.00283 0.0000 0.9179 0.9182
0.250 0.0580 0.00811 0.00283 -0.0057 0.8869 0.9389
0.500 0.1067 0.00815 0.00280 -0.0097 0.8481 0.9504
0.750 0.1485 0.00825 0.00276 -0.0120 0.7919 0.9605
1.000 0.1877 0.00848 0.00272 -0.0138 0.7204 0.9679
1.250 0.2208 0.00878 0.00271 -0.0146 0.6448 0.9761
1.500 0.2529 0.00911 0.00273 -0.0153 0.5729 0.9839
1.750 0.2871 0.00948 0.00278 -0.0167 0.4930 0.9912
2.000 0.3232 0.00987 0.00286 -0.0186 0.4188 0.9988
2.250 0.3465 0.01018 0.00294 -0.0179 0.3626 1.0000
2.500 0.3667 0.01049 0.00304 -0.0164 0.3126 1.0000
3.000 0.4085 0.01109 0.00334 -0.0138 0.2388 1.0000
3.250 0.4299 0.01140 0.00353 -0.0126 0.2110 1.0000
3.500 0.4515 0.01169 0.00373 -0.0114 0.1874 1.0000
3.750 0.4733 0.01200 0.00396 -0.0103 0.1681 1.0000
4.000 0.4954 0.01228 0.00421 -0.0092 0.1519 1.0000
4.250 0.5177 0.01257 0.00447 -0.0081 0.1364 1.0000
4.500 0.5401 0.01287 0.00474 -0.0070 0.1207 1.0000
4.750 0.5625 0.01320 0.00506 -0.0059 0.1042 1.0000
5.000 0.5846 0.01359 0.00538 -0.0048 0.0859 1.0000
5.250 0.6065 0.01404 0.00577 -0.0037 0.0705 1.0000
5.500 0.6280 0.01457 0.00625 -0.0025 0.0583 1.0000
5.750 0.6498 0.01509 0.00680 -0.0013 0.0498 1.0000
6.000 0.6713 0.01567 0.00742 -0.0001 0.0443 1.0000
6.250 0.6929 0.01624 0.00802 0.0010 0.0392 1.0000
6.500 0.7136 0.01696 0.00879 0.0023 0.0355 1.0000
6.750 0.7348 0.01762 0.00955 0.0036 0.0329 1.0000
7.000 0.7557 0.01831 0.01032 0.0048 0.0302 1.0000
7.250 0.7747 0.01931 0.01135 0.0062 0.0278 1.0000
7.500 0.7958 0.02005 0.01224 0.0074 0.0260 1.0000
7.750 0.8158 0.02097 0.01328 0.0087 0.0245 1.0000
8.000 0.8355 0.02192 0.01432 0.0100 0.0230 1.0000
8.250 0.8544 0.02296 0.01543 0.0113 0.0219 1.0000
8.500 0.8720 0.02429 0.01691 0.0127 0.0207 1.0000
8.750 0.8908 0.02543 0.01828 0.0140 0.0196 1.0000
9.000 0.9083 0.02674 0.01979 0.0154 0.0186 1.0000
9.250 0.9246 0.02821 0.02147 0.0169 0.0178 1.0000
9.500 0.9402 0.02962 0.02305 0.0183 0.0171 1.0000
9.750 0.9540 0.03125 0.02487 0.0198 0.0167 1.0000
10.000 0.9661 0.03295 0.02674 0.0213 0.0162 1.0000
10.250 0.9737 0.03526 0.02926 0.0231 0.0158 1.0000
10.500 0.9765 0.03803 0.03236 0.0252 0.0156 1.0000
10.750 0.9759 0.04080 0.03548 0.0273 0.0154 1.0000
11.000 0.9672 0.04393 0.03896 0.0297 0.0151 1.0000
11.250 0.9502 0.04734 0.04266 0.0319 0.0150 1.0000
11.500 0.9332 0.05139 0.04693 0.0317 0.0151 1.0000
11.750 0.9139 0.05697 0.05275 0.0280 0.0150 1.0000
12.000 0.8900 0.06562 0.06159 0.0203 0.0153 1.0000
12.250 0.8679 0.07560 0.07169 0.0120 0.0155 1.0000
12.500 0.8236 0.09139 0.08757 0.0011 0.0157 1.0000
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Polar data table (+)
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