FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il) Reynolds number: 200,000 Max Cl/Cd: 39.08 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx711525-il-200000-n5.txt Download as CSV file: xf-fx711525-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/25 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-17.250 -0.8610 0.13544 0.13105 0.0104 1.0000 0.0180
-17.000 -0.9068 0.11955 0.11488 0.0004 1.0000 0.0178
-16.750 -0.9364 0.10856 0.10365 -0.0065 1.0000 0.0177
-16.500 -0.9554 0.10049 0.09538 -0.0114 1.0000 0.0176
-16.250 -0.9741 0.09289 0.08757 -0.0158 1.0000 0.0176
-16.000 -0.9875 0.08664 0.08113 -0.0193 1.0000 0.0175
-15.750 -1.0000 0.08084 0.07512 -0.0222 1.0000 0.0176
-15.500 -1.0079 0.07602 0.07014 -0.0244 1.0000 0.0176
-15.250 -1.0166 0.07130 0.06520 -0.0266 1.0000 0.0178
-15.000 -1.0205 0.06742 0.06117 -0.0280 1.0000 0.0178
-14.750 -1.0231 0.06387 0.05746 -0.0291 1.0000 0.0178
-14.500 -1.0250 0.06056 0.05399 -0.0299 1.0000 0.0179
-14.250 -1.0250 0.05756 0.05083 -0.0305 1.0000 0.0180
-14.000 -1.0227 0.05490 0.04803 -0.0308 1.0000 0.0181
-13.750 -1.0193 0.05241 0.04539 -0.0310 1.0000 0.0182
-13.500 -1.0143 0.05012 0.04299 -0.0310 1.0000 0.0182
-13.250 -1.0081 0.04803 0.04084 -0.0309 1.0000 0.0183
-13.000 -1.0012 0.04606 0.03880 -0.0307 1.0000 0.0184
-12.750 -0.9942 0.04416 0.03684 -0.0305 1.0000 0.0185
-12.500 -0.9867 0.04232 0.03495 -0.0302 1.0000 0.0186
-12.250 -0.9785 0.04060 0.03317 -0.0298 1.0000 0.0187
-12.000 -0.9701 0.03893 0.03144 -0.0294 1.0000 0.0188
-11.750 -0.9613 0.03733 0.02979 -0.0289 1.0000 0.0189
-11.500 -0.9525 0.03576 0.02817 -0.0284 1.0000 0.0191
-11.250 -0.9433 0.03426 0.02662 -0.0278 1.0000 0.0193
-11.000 -0.9336 0.03283 0.02514 -0.0272 1.0000 0.0195
-10.750 -0.9237 0.03144 0.02370 -0.0265 1.0000 0.0197
-10.500 -0.9135 0.03011 0.02233 -0.0258 1.0000 0.0199
-10.250 -0.9033 0.02881 0.02098 -0.0250 1.0000 0.0201
-10.000 -0.8779 0.02752 0.01952 -0.0272 0.8847 0.0204
-9.750 -0.8622 0.02642 0.01822 -0.0271 0.8579 0.0208
-9.250 -0.8381 0.02448 0.01606 -0.0250 0.8343 0.0215
-9.000 -0.8264 0.02365 0.01512 -0.0236 0.8263 0.0222
-8.750 -0.8149 0.02292 0.01431 -0.0217 0.8193 0.0228
-8.500 -0.8031 0.02231 0.01360 -0.0198 0.8128 0.0235
-8.250 -0.7886 0.02170 0.01288 -0.0181 0.8075 0.0246
-8.000 -0.7723 0.02105 0.01218 -0.0169 0.8026 0.0259
-7.750 -0.7544 0.02048 0.01153 -0.0157 0.7975 0.0279
-7.500 -0.7369 0.01988 0.01088 -0.0145 0.7927 0.0306
-7.250 -0.7185 0.01931 0.01028 -0.0133 0.7883 0.0348
-7.000 -0.6993 0.01872 0.00973 -0.0124 0.7836 0.0422
-6.750 -0.6793 0.01819 0.00921 -0.0114 0.7790 0.0536
-6.500 -0.6600 0.01761 0.00871 -0.0104 0.7750 0.0696
-6.250 -0.6394 0.01704 0.00823 -0.0096 0.7704 0.0904
-6.000 -0.6194 0.01639 0.00775 -0.0088 0.7656 0.1190
-5.750 -0.5982 0.01585 0.00730 -0.0080 0.7614 0.1456
-5.500 -0.5769 0.01532 0.00689 -0.0073 0.7580 0.1793
-5.250 -0.5561 0.01463 0.00645 -0.0066 0.7534 0.2269
-5.000 -0.5363 0.01388 0.00600 -0.0057 0.7487 0.2896
-4.750 -0.5163 0.01321 0.00565 -0.0047 0.7444 0.3564
-4.250 -0.4695 0.01252 0.00536 -0.0033 0.7362 0.4583
-4.000 -0.4441 0.01238 0.00533 -0.0028 0.7318 0.4974
-3.750 -0.4182 0.01232 0.00534 -0.0022 0.7277 0.5287
-3.500 -0.3917 0.01230 0.00529 -0.0018 0.7241 0.5520
-3.250 -0.3645 0.01228 0.00526 -0.0015 0.7198 0.5676
-3.000 -0.3369 0.01225 0.00528 -0.0013 0.7149 0.5779
-2.750 -0.3093 0.01223 0.00522 -0.0011 0.7104 0.5893
-2.500 -0.2817 0.01225 0.00523 -0.0007 0.7064 0.5985
-2.250 -0.2538 0.01223 0.00515 -0.0006 0.7022 0.6075
-2.000 -0.2257 0.01224 0.00520 -0.0005 0.6968 0.6143
-1.750 -0.1976 0.01223 0.00513 -0.0004 0.6918 0.6223
-1.500 -0.1696 0.01221 0.00508 -0.0003 0.6876 0.6285
-1.250 -0.1415 0.01221 0.00506 -0.0001 0.6839 0.6339
-1.000 -0.1131 0.01220 0.00505 -0.0002 0.6784 0.6397
-0.750 -0.0848 0.01219 0.00500 -0.0002 0.6737 0.6459
-0.500 -0.0566 0.01220 0.00503 -0.0001 0.6695 0.6504
-0.250 -0.0284 0.01220 0.00501 0.0001 0.6658 0.6553
0.000 0.0000 0.01220 0.00502 0.0000 0.6607 0.6607
0.250 0.0284 0.01220 0.00501 -0.0001 0.6553 0.6658
0.500 0.0566 0.01220 0.00504 0.0001 0.6504 0.6695
0.750 0.0848 0.01219 0.00500 0.0002 0.6459 0.6737
1.000 0.1131 0.01220 0.00505 0.0002 0.6397 0.6784
1.250 0.1415 0.01221 0.00506 0.0001 0.6339 0.6839
1.500 0.1696 0.01221 0.00508 0.0003 0.6285 0.6876
1.750 0.1976 0.01223 0.00513 0.0004 0.6223 0.6918
2.000 0.2257 0.01224 0.00520 0.0005 0.6144 0.6968
2.250 0.2538 0.01223 0.00515 0.0006 0.6075 0.7022
2.500 0.2817 0.01225 0.00523 0.0007 0.5985 0.7064
2.750 0.3093 0.01223 0.00522 0.0011 0.5893 0.7104
3.000 0.3369 0.01225 0.00528 0.0013 0.5778 0.7149
3.250 0.3645 0.01228 0.00526 0.0015 0.5673 0.7198
3.500 0.3917 0.01230 0.00529 0.0018 0.5519 0.7241
3.750 0.4182 0.01232 0.00534 0.0022 0.5280 0.7278
4.000 0.4441 0.01238 0.00533 0.0028 0.4969 0.7318
4.250 0.4694 0.01252 0.00536 0.0033 0.4574 0.7362
4.750 0.5163 0.01321 0.00565 0.0047 0.3563 0.7444
5.000 0.5364 0.01388 0.00600 0.0057 0.2899 0.7487
5.250 0.5562 0.01463 0.00645 0.0066 0.2270 0.7534
5.500 0.5770 0.01531 0.00688 0.0072 0.1796 0.7580
5.750 0.5982 0.01585 0.00730 0.0080 0.1456 0.7614
6.000 0.6194 0.01640 0.00775 0.0088 0.1187 0.7656
6.250 0.6395 0.01704 0.00823 0.0096 0.0905 0.7704
6.500 0.6602 0.01760 0.00870 0.0104 0.0703 0.7750
6.750 0.6794 0.01818 0.00921 0.0114 0.0542 0.7791
7.000 0.6993 0.01872 0.00973 0.0123 0.0420 0.7836
7.250 0.7184 0.01932 0.01029 0.0133 0.0343 0.7883
7.500 0.7370 0.01988 0.01088 0.0145 0.0306 0.7927
7.750 0.7547 0.02047 0.01152 0.0157 0.0280 0.7975
8.000 0.7723 0.02106 0.01219 0.0169 0.0259 0.8026
8.250 0.7887 0.02169 0.01288 0.0181 0.0246 0.8075
8.500 0.8032 0.02231 0.01359 0.0197 0.0236 0.8128
8.750 0.8150 0.02293 0.01431 0.0217 0.0228 0.8193
9.000 0.8265 0.02365 0.01512 0.0235 0.0223 0.8263
9.250 0.8384 0.02448 0.01605 0.0250 0.0217 0.8343
9.750 0.8625 0.02642 0.01822 0.0271 0.0208 0.8578
10.250 0.9034 0.02882 0.02099 0.0250 0.0201 1.0000
10.500 0.9141 0.03008 0.02230 0.0257 0.0199 1.0000
10.750 0.9241 0.03143 0.02370 0.0264 0.0196 1.0000
11.000 0.9343 0.03280 0.02511 0.0271 0.0195 1.0000
11.250 0.9437 0.03426 0.02662 0.0277 0.0193 1.0000
11.500 0.9533 0.03573 0.02814 0.0283 0.0191 1.0000
11.750 0.9621 0.03730 0.02976 0.0288 0.0189 1.0000
12.000 0.9710 0.03889 0.03141 0.0293 0.0188 1.0000
12.250 0.9793 0.04058 0.03315 0.0297 0.0187 1.0000
12.500 0.9873 0.04232 0.03494 0.0301 0.0186 1.0000
12.750 0.9952 0.04412 0.03680 0.0304 0.0185 1.0000
13.000 1.0023 0.04602 0.03876 0.0306 0.0184 1.0000
13.250 1.0089 0.04802 0.04082 0.0308 0.0183 1.0000
13.500 1.0154 0.05008 0.04296 0.0309 0.0183 1.0000
13.750 1.0204 0.05235 0.04534 0.0309 0.0182 1.0000
14.000 1.0239 0.05485 0.04797 0.0307 0.0181 1.0000
14.250 1.0263 0.05750 0.05076 0.0304 0.0180 1.0000
14.500 1.0261 0.06052 0.05394 0.0298 0.0179 1.0000
14.750 1.0252 0.06372 0.05729 0.0290 0.0179 1.0000
15.000 1.0231 0.06719 0.06092 0.0280 0.0179 1.0000
15.250 1.0174 0.07129 0.06520 0.0264 0.0177 1.0000
15.500 1.0116 0.07560 0.06968 0.0246 0.0177 1.0000
15.750 1.0010 0.08083 0.07511 0.0221 0.0176 1.0000
16.000 0.9893 0.08648 0.08096 0.0192 0.0175 1.0000
16.250 0.9764 0.09265 0.08732 0.0158 0.0176 1.0000
16.500 0.9577 0.10023 0.09511 0.0114 0.0176 1.0000
16.750 0.9363 0.10884 0.10394 0.0061 0.0176 1.0000
17.000 0.9067 0.11987 0.11521 -0.0008 0.0178 1.0000
17.250 0.8697 0.13351 0.12908 -0.0093 0.0180 1.0000
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Polar data table (+)
Polar graphs
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