FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il) Reynolds number: 100,000 Max Cl/Cd: 34.18 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx711525-il-100000-n5.txt Download as CSV file: xf-fx711525-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8575 0.10235 0.09611 -0.0136 1.0000 0.0278
-15.000 -0.8835 0.09359 0.08710 -0.0191 1.0000 0.0276
-14.750 -0.9015 0.08691 0.08023 -0.0229 1.0000 0.0276
-14.500 -0.9184 0.08091 0.07402 -0.0260 1.0000 0.0275
-14.250 -0.9336 0.07549 0.06837 -0.0284 1.0000 0.0275
-14.000 -0.9449 0.07085 0.06351 -0.0302 1.0000 0.0275
-13.750 -0.9545 0.06655 0.05898 -0.0315 1.0000 0.0275
-13.500 -0.9608 0.06275 0.05494 -0.0323 1.0000 0.0276
-13.250 -0.9638 0.05938 0.05134 -0.0328 1.0000 0.0277
-13.000 -0.9616 0.05657 0.04838 -0.0329 1.0000 0.0278
-12.750 -0.9558 0.05418 0.04589 -0.0329 1.0000 0.0280
-12.500 -0.9488 0.05192 0.04353 -0.0327 1.0000 0.0283
-12.250 -0.9407 0.04981 0.04131 -0.0324 1.0000 0.0285
-12.000 -0.9313 0.04783 0.03923 -0.0321 1.0000 0.0288
-11.750 -0.9208 0.04597 0.03728 -0.0317 1.0000 0.0291
-11.500 -0.9096 0.04417 0.03539 -0.0312 1.0000 0.0296
-11.250 -0.8976 0.04249 0.03361 -0.0306 1.0000 0.0301
-11.000 -0.8851 0.04090 0.03192 -0.0300 1.0000 0.0307
-10.750 -0.8725 0.03936 0.03027 -0.0293 1.0000 0.0313
-10.500 -0.8615 0.03784 0.02875 -0.0286 1.0000 0.0318
-10.250 -0.8512 0.03634 0.02724 -0.0280 1.0000 0.0325
-10.000 -0.8405 0.03493 0.02580 -0.0273 1.0000 0.0332
-9.750 -0.8299 0.03353 0.02434 -0.0265 1.0000 0.0347
-9.500 -0.8197 0.03217 0.02297 -0.0257 1.0000 0.0361
-9.250 -0.8095 0.03086 0.02165 -0.0249 1.0000 0.0376
-9.000 -0.7995 0.02961 0.02038 -0.0239 1.0000 0.0400
-8.750 -0.7900 0.02844 0.01922 -0.0227 1.0000 0.0424
-8.500 -0.7809 0.02735 0.01812 -0.0212 1.0000 0.0453
-8.250 -0.7710 0.02629 0.01707 -0.0198 0.9757 0.0497
-8.000 -0.7442 0.02503 0.01578 -0.0215 0.9256 0.0581
-7.750 -0.7216 0.02399 0.01473 -0.0220 0.9032 0.0693
-7.500 -0.7029 0.02311 0.01384 -0.0215 0.8871 0.0857
-7.250 -0.6869 0.02222 0.01305 -0.0205 0.8748 0.1066
-7.000 -0.6705 0.02144 0.01233 -0.0194 0.8648 0.1321
-6.750 -0.6548 0.02062 0.01165 -0.0182 0.8559 0.1651
-6.500 -0.6407 0.01971 0.01097 -0.0168 0.8477 0.2106
-6.250 -0.6271 0.01878 0.01036 -0.0152 0.8403 0.2719
-6.000 -0.6133 0.01793 0.00993 -0.0135 0.8330 0.3464
-5.750 -0.5955 0.01751 0.00985 -0.0119 0.8268 0.4159
-5.500 -0.5737 0.01744 0.00996 -0.0106 0.8207 0.4653
-5.250 -0.5502 0.01749 0.01002 -0.0096 0.8142 0.5001
-5.000 -0.5258 0.01761 0.01007 -0.0086 0.8088 0.5253
-4.750 -0.5007 0.01770 0.01008 -0.0079 0.8035 0.5453
-4.500 -0.4751 0.01783 0.01015 -0.0073 0.7979 0.5617
-4.250 -0.4490 0.01801 0.01025 -0.0065 0.7927 0.5762
-4.000 -0.4232 0.01816 0.01031 -0.0059 0.7875 0.5901
-3.750 -0.3962 0.01841 0.01053 -0.0053 0.7816 0.6013
-3.500 -0.3698 0.01858 0.01062 -0.0047 0.7767 0.6114
-3.250 -0.3438 0.01871 0.01066 -0.0041 0.7719 0.6215
-3.000 -0.3172 0.01879 0.01071 -0.0038 0.7658 0.6296
-2.750 -0.2906 0.01892 0.01078 -0.0032 0.7606 0.6367
-2.500 -0.2653 0.01886 0.01060 -0.0029 0.7556 0.6459
-2.250 -0.2379 0.01901 0.01077 -0.0026 0.7496 0.6511
-2.000 -0.2115 0.01905 0.01075 -0.0021 0.7445 0.6576
-1.750 -0.1860 0.01895 0.01053 -0.0019 0.7399 0.6653
-1.500 -0.1589 0.01903 0.01065 -0.0016 0.7336 0.6695
-1.250 -0.1323 0.01907 0.01066 -0.0012 0.7283 0.6751
-1.000 -0.1064 0.01900 0.01050 -0.0009 0.7241 0.6827
-0.750 -0.0797 0.01903 0.01054 -0.0007 0.7185 0.6874
-0.500 -0.0530 0.01906 0.01060 -0.0004 0.7126 0.6920
-0.250 -0.0265 0.01904 0.01054 -0.0002 0.7079 0.6978
0.000 0.0000 0.01897 0.01039 0.0000 0.7043 0.7043
0.250 0.0265 0.01904 0.01054 0.0001 0.6978 0.7079
0.500 0.0530 0.01906 0.01059 0.0004 0.6920 0.7126
0.750 0.0797 0.01903 0.01054 0.0007 0.6874 0.7185
1.000 0.1064 0.01900 0.01050 0.0009 0.6827 0.7241
1.250 0.1323 0.01907 0.01066 0.0012 0.6751 0.7284
1.500 0.1589 0.01903 0.01065 0.0016 0.6695 0.7336
1.750 0.1860 0.01895 0.01053 0.0019 0.6653 0.7399
2.000 0.2115 0.01905 0.01075 0.0021 0.6576 0.7445
2.250 0.2379 0.01901 0.01077 0.0026 0.6510 0.7497
2.500 0.2653 0.01886 0.01060 0.0029 0.6459 0.7556
2.750 0.2906 0.01892 0.01078 0.0032 0.6367 0.7606
3.000 0.3173 0.01879 0.01071 0.0038 0.6296 0.7658
3.250 0.3438 0.01871 0.01066 0.0041 0.6215 0.7720
3.500 0.3698 0.01858 0.01062 0.0046 0.6115 0.7767
3.750 0.3962 0.01841 0.01053 0.0053 0.6013 0.7816
4.000 0.4232 0.01817 0.01031 0.0058 0.5901 0.7875
4.250 0.4490 0.01801 0.01025 0.0065 0.5763 0.7927
4.500 0.4751 0.01783 0.01015 0.0073 0.5616 0.7979
4.750 0.5008 0.01770 0.01008 0.0079 0.5452 0.8035
5.000 0.5258 0.01761 0.01007 0.0086 0.5252 0.8088
5.250 0.5502 0.01749 0.01002 0.0096 0.5002 0.8142
5.500 0.5737 0.01744 0.00996 0.0106 0.4653 0.8207
5.750 0.5955 0.01751 0.00985 0.0119 0.4158 0.8269
6.000 0.6131 0.01794 0.00993 0.0135 0.3454 0.8330
6.250 0.6270 0.01879 0.01036 0.0152 0.2712 0.8404
6.500 0.6407 0.01972 0.01098 0.0167 0.2100 0.8476
6.750 0.6549 0.02062 0.01164 0.0182 0.1651 0.8559
7.000 0.6706 0.02144 0.01234 0.0194 0.1319 0.8648
7.250 0.6868 0.02224 0.01306 0.0205 0.1057 0.8748
7.500 0.7030 0.02311 0.01384 0.0215 0.0855 0.8871
7.750 0.7218 0.02399 0.01472 0.0220 0.0694 0.9032
8.000 0.7443 0.02504 0.01579 0.0215 0.0577 0.9257
8.250 0.7712 0.02629 0.01706 0.0197 0.0497 0.9763
8.500 0.7813 0.02734 0.01812 0.0212 0.0454 1.0000
8.750 0.7903 0.02844 0.01922 0.0227 0.0423 1.0000
9.000 0.7996 0.02963 0.02039 0.0239 0.0401 1.0000
9.250 0.8097 0.03088 0.02167 0.0249 0.0380 1.0000
9.500 0.8199 0.03218 0.02299 0.0257 0.0362 1.0000
9.750 0.8301 0.03354 0.02435 0.0265 0.0347 1.0000
10.000 0.8411 0.03492 0.02578 0.0272 0.0335 1.0000
10.250 0.8516 0.03635 0.02725 0.0279 0.0325 1.0000
10.500 0.8623 0.03781 0.02873 0.0286 0.0319 1.0000
10.750 0.8731 0.03936 0.03028 0.0292 0.0312 1.0000
11.000 0.8858 0.04086 0.03188 0.0299 0.0307 1.0000
11.250 0.8983 0.04249 0.03360 0.0305 0.0301 1.0000
11.500 0.9105 0.04415 0.03536 0.0311 0.0297 1.0000
11.750 0.9217 0.04595 0.03725 0.0316 0.0292 1.0000
12.000 0.9323 0.04780 0.03920 0.0320 0.0289 1.0000
12.250 0.9415 0.04980 0.04130 0.0324 0.0285 1.0000
12.500 0.9498 0.05191 0.04351 0.0326 0.0282 1.0000
12.750 0.9566 0.05417 0.04588 0.0328 0.0280 1.0000
13.000 0.9624 0.05658 0.04840 0.0328 0.0278 1.0000
13.250 0.9638 0.05948 0.05146 0.0327 0.0277 1.0000
13.500 0.9621 0.06270 0.05488 0.0323 0.0276 1.0000
13.750 0.9561 0.06647 0.05888 0.0314 0.0275 1.0000
14.000 0.9464 0.07078 0.06343 0.0301 0.0275 1.0000
14.250 0.9357 0.07536 0.06823 0.0284 0.0275 1.0000
14.500 0.9208 0.08070 0.07379 0.0260 0.0275 1.0000
14.750 0.9039 0.08670 0.08000 0.0229 0.0276 1.0000
15.000 0.8859 0.09336 0.08687 0.0191 0.0277 1.0000
15.250 0.8513 0.10384 0.09765 0.0124 0.0279 1.0000
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