FX 71-L-150/30 AIRFOIL (fx71l150-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 71-L-150/30 AIRFOIL (fx71l150-il) Reynolds number: 50,000 Max Cl/Cd: 26.93 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx71l150-il-50000-n5.txt Download as CSV file: xf-fx71l150-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/30 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.7298 0.10912 0.10119 -0.0115 1.0000 0.0510
-13.500 -0.7733 0.09618 0.08802 -0.0196 1.0000 0.0501
-13.250 -0.8083 0.08672 0.07829 -0.0252 1.0000 0.0498
-13.000 -0.8321 0.07984 0.07116 -0.0287 1.0000 0.0496
-12.750 -0.8478 0.07447 0.06556 -0.0308 1.0000 0.0496
-12.500 -0.8578 0.06996 0.06082 -0.0321 1.0000 0.0499
-12.250 -0.8632 0.06605 0.05669 -0.0329 1.0000 0.0504
-12.000 -0.8646 0.06254 0.05295 -0.0333 1.0000 0.0511
-11.750 -0.8619 0.05938 0.04953 -0.0333 1.0000 0.0519
-11.500 -0.8565 0.05641 0.04624 -0.0331 1.0000 0.0532
-11.250 -0.8433 0.05439 0.04420 -0.0328 1.0000 0.0549
-11.000 -0.8311 0.05240 0.04213 -0.0324 1.0000 0.0572
-10.750 -0.8165 0.05036 0.03987 -0.0318 1.0000 0.0603
-10.500 -0.8014 0.04875 0.03830 -0.0313 1.0000 0.0635
-10.250 -0.7834 0.04714 0.03655 -0.0305 1.0000 0.0677
-10.000 -0.7688 0.04557 0.03499 -0.0297 1.0000 0.0720
-9.750 -0.7549 0.04394 0.03334 -0.0289 1.0000 0.0777
-9.500 -0.7440 0.04226 0.03163 -0.0282 1.0000 0.0855
-9.250 -0.7370 0.04044 0.02991 -0.0276 1.0000 0.0957
-9.000 -0.7301 0.03869 0.02826 -0.0270 1.0000 0.1072
-8.750 -0.7237 0.03693 0.02661 -0.0261 1.0000 0.1212
-8.500 -0.7179 0.03520 0.02503 -0.0250 1.0000 0.1363
-8.250 -0.7137 0.03350 0.02350 -0.0236 1.0000 0.1538
-8.000 -0.7110 0.03190 0.02207 -0.0217 1.0000 0.1746
-7.750 -0.7101 0.03035 0.02080 -0.0195 1.0000 0.1993
-7.500 -0.7086 0.02887 0.01961 -0.0174 1.0000 0.2339
-7.250 -0.7077 0.02756 0.01870 -0.0149 1.0000 0.2760
-7.000 -0.7063 0.02664 0.01818 -0.0119 1.0000 0.3224
-6.750 -0.7066 0.02624 0.01810 -0.0080 1.0000 0.3642
-6.500 -0.6874 0.02621 0.01828 -0.0069 0.9821 0.4156
-6.000 -0.6188 0.02710 0.01900 -0.0087 0.9517 0.5003
-5.750 -0.5827 0.02793 0.01967 -0.0090 0.9398 0.5263
-5.500 -0.5465 0.02867 0.02023 -0.0095 0.9298 0.5484
-5.250 -0.5124 0.02927 0.02066 -0.0097 0.9202 0.5669
-5.000 -0.4809 0.02963 0.02081 -0.0099 0.9111 0.5837
-4.750 -0.4531 0.02974 0.02073 -0.0099 0.9016 0.5999
-4.500 -0.4168 0.03025 0.02110 -0.0102 0.8940 0.6100
-4.250 -0.3904 0.03025 0.02094 -0.0099 0.8847 0.6221
-4.000 -0.3683 0.03007 0.02058 -0.0093 0.8756 0.6352
-3.750 -0.3395 0.03019 0.02058 -0.0090 0.8675 0.6444
-3.500 -0.3160 0.03003 0.02029 -0.0085 0.8597 0.6546
-3.250 -0.2972 0.02973 0.01986 -0.0076 0.8513 0.6659
-3.000 -0.2673 0.02980 0.01983 -0.0074 0.8449 0.6732
-2.750 -0.2469 0.02961 0.01955 -0.0065 0.8371 0.6829
-2.500 -0.2237 0.02942 0.01924 -0.0060 0.8309 0.6920
-2.250 -0.2014 0.02933 0.01909 -0.0053 0.8236 0.6992
-2.000 -0.1817 0.02903 0.01869 -0.0046 0.8178 0.7082
-1.750 -0.1592 0.02896 0.01858 -0.0040 0.8108 0.7152
-1.500 -0.1370 0.02879 0.01835 -0.0033 0.8045 0.7232
-1.250 -0.1175 0.02865 0.01815 -0.0024 0.7973 0.7318
-1.000 -0.0910 0.02860 0.01807 -0.0020 0.7907 0.7378
-0.750 -0.0713 0.02844 0.01787 -0.0012 0.7836 0.7460
-0.500 -0.0444 0.02843 0.01786 -0.0010 0.7769 0.7512
-0.250 -0.0238 0.02836 0.01775 -0.0003 0.7703 0.7585
0.000 0.0000 0.02837 0.01777 0.0000 0.7638 0.7638
0.250 0.0238 0.02836 0.01774 0.0003 0.7585 0.7703
0.500 0.0444 0.02843 0.01785 0.0010 0.7512 0.7769
0.750 0.0713 0.02844 0.01787 0.0012 0.7460 0.7836
1.000 0.0910 0.02859 0.01807 0.0020 0.7378 0.7907
1.250 0.1175 0.02865 0.01815 0.0024 0.7318 0.7973
1.500 0.1370 0.02879 0.01835 0.0033 0.7232 0.8045
1.750 0.1592 0.02896 0.01858 0.0040 0.7152 0.8108
2.000 0.1817 0.02903 0.01869 0.0046 0.7082 0.8178
2.250 0.2014 0.02932 0.01909 0.0053 0.6992 0.8236
2.500 0.2237 0.02942 0.01923 0.0060 0.6920 0.8309
2.750 0.2469 0.02962 0.01955 0.0065 0.6829 0.8371
3.000 0.2673 0.02980 0.01982 0.0074 0.6732 0.8449
3.250 0.2973 0.02972 0.01985 0.0076 0.6659 0.8513
3.500 0.3161 0.03003 0.02029 0.0085 0.6546 0.8596
3.750 0.3396 0.03018 0.02057 0.0090 0.6444 0.8675
4.000 0.3684 0.03006 0.02057 0.0093 0.6352 0.8756
4.250 0.3905 0.03024 0.02093 0.0099 0.6221 0.8847
4.500 0.4169 0.03024 0.02109 0.0102 0.6100 0.8940
4.750 0.4532 0.02973 0.02072 0.0099 0.5999 0.9016
5.000 0.4810 0.02962 0.02080 0.0099 0.5837 0.9112
5.250 0.5126 0.02926 0.02065 0.0097 0.5669 0.9203
5.500 0.5466 0.02866 0.02022 0.0095 0.5484 0.9299
5.750 0.5828 0.02792 0.01966 0.0090 0.5262 0.9399
6.000 0.6189 0.02710 0.01900 0.0086 0.5004 0.9518
6.500 0.6876 0.02621 0.01827 0.0069 0.4155 0.9822
6.750 0.7065 0.02623 0.01810 0.0080 0.3643 1.0000
7.000 0.7063 0.02664 0.01817 0.0119 0.3223 1.0000
7.250 0.7078 0.02756 0.01869 0.0149 0.2758 1.0000
7.500 0.7087 0.02887 0.01960 0.0174 0.2338 1.0000
7.750 0.7103 0.03035 0.02080 0.0195 0.1992 1.0000
8.000 0.7113 0.03190 0.02206 0.0216 0.1746 1.0000
8.250 0.7140 0.03350 0.02350 0.0235 0.1536 1.0000
8.500 0.7183 0.03520 0.02503 0.0249 0.1362 1.0000
8.750 0.7237 0.03695 0.02662 0.0261 0.1207 1.0000
9.000 0.7303 0.03870 0.02826 0.0269 0.1070 1.0000
9.250 0.7374 0.04044 0.02990 0.0275 0.0956 1.0000
9.500 0.7447 0.04224 0.03161 0.0281 0.0855 1.0000
9.750 0.7555 0.04393 0.03333 0.0288 0.0777 1.0000
10.000 0.7696 0.04554 0.03495 0.0297 0.0721 1.0000
10.250 0.7841 0.04713 0.03654 0.0304 0.0677 1.0000
10.500 0.8019 0.04876 0.03831 0.0312 0.0633 1.0000
10.750 0.8181 0.05033 0.03985 0.0318 0.0605 1.0000
11.000 0.8321 0.05237 0.04210 0.0323 0.0573 1.0000
11.250 0.8447 0.05438 0.04420 0.0327 0.0550 1.0000
11.500 0.8579 0.05635 0.04618 0.0330 0.0533 1.0000
11.750 0.8629 0.05938 0.04954 0.0332 0.0519 1.0000
12.000 0.8659 0.06250 0.05291 0.0332 0.0511 1.0000
12.250 0.8641 0.06606 0.05670 0.0328 0.0504 1.0000
12.500 0.8587 0.06997 0.06084 0.0320 0.0500 1.0000
12.750 0.8488 0.07448 0.06558 0.0307 0.0497 1.0000
13.000 0.8331 0.07985 0.07118 0.0286 0.0495 1.0000
13.250 0.8093 0.08673 0.07830 0.0251 0.0497 1.0000
13.500 0.7748 0.09611 0.08794 0.0195 0.0502 1.0000
13.750 0.7306 0.10923 0.10129 0.0113 0.0510 1.0000
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