FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il) Reynolds number: 50,000 Max Cl/Cd: 25.55 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx711520-il-50000-n5.txt Download as CSV file: xf-fx711520-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 71-L-150/20 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7538 0.10547 0.09763 -0.0087 1.0000 0.0501
-13.250 -0.7890 0.09473 0.08668 -0.0155 1.0000 0.0494
-13.000 -0.8197 0.08617 0.07790 -0.0205 1.0000 0.0490
-12.750 -0.8424 0.07952 0.07101 -0.0239 1.0000 0.0488
-12.500 -0.8587 0.07410 0.06534 -0.0261 1.0000 0.0489
-12.250 -0.8698 0.06949 0.06049 -0.0275 1.0000 0.0491
-12.000 -0.8757 0.06550 0.05625 -0.0283 1.0000 0.0494
-11.750 -0.8770 0.06195 0.05245 -0.0287 1.0000 0.0499
-11.500 -0.8734 0.05878 0.04902 -0.0288 1.0000 0.0506
-11.250 -0.8653 0.05589 0.04583 -0.0286 1.0000 0.0514
-11.000 -0.8486 0.05381 0.04369 -0.0283 1.0000 0.0528
-10.750 -0.8305 0.05194 0.04172 -0.0278 1.0000 0.0544
-10.500 -0.8091 0.05016 0.03972 -0.0271 1.0000 0.0568
-10.250 -0.7902 0.04865 0.03824 -0.0265 1.0000 0.0594
-10.000 -0.7721 0.04711 0.03656 -0.0259 1.0000 0.0634
-9.750 -0.7582 0.04552 0.03501 -0.0254 1.0000 0.0676
-9.500 -0.7442 0.04392 0.03343 -0.0249 1.0000 0.0728
-9.250 -0.7318 0.04225 0.03177 -0.0243 1.0000 0.0798
-9.000 -0.7221 0.04048 0.03005 -0.0238 1.0000 0.0893
-8.750 -0.7137 0.03870 0.02838 -0.0234 1.0000 0.1011
-8.500 -0.7062 0.03691 0.02675 -0.0230 1.0000 0.1155
-8.250 -0.7005 0.03506 0.02507 -0.0224 1.0000 0.1327
-8.000 -0.6966 0.03323 0.02345 -0.0215 1.0000 0.1528
-7.750 -0.6950 0.03150 0.02196 -0.0202 1.0000 0.1766
-7.500 -0.6936 0.02984 0.02063 -0.0187 1.0000 0.2069
-7.250 -0.6938 0.02833 0.01950 -0.0168 1.0000 0.2474
-7.000 -0.6922 0.02709 0.01874 -0.0149 0.9844 0.3012
-6.750 -0.6670 0.02674 0.01892 -0.0150 0.9549 0.3827
-6.500 -0.6331 0.02727 0.01954 -0.0153 0.9391 0.4402
-6.250 -0.6003 0.02796 0.02009 -0.0154 0.9264 0.4810
-6.000 -0.5686 0.02861 0.02052 -0.0155 0.9160 0.5114
-5.750 -0.5369 0.02950 0.02121 -0.0149 0.9060 0.5334
-5.250 -0.4776 0.03081 0.02211 -0.0137 0.8883 0.5695
-5.000 -0.4528 0.03105 0.02215 -0.0130 0.8803 0.5863
-4.750 -0.4211 0.03173 0.02268 -0.0121 0.8731 0.5973
-4.500 -0.3978 0.03176 0.02255 -0.0114 0.8654 0.6096
-4.250 -0.3738 0.03179 0.02240 -0.0106 0.8587 0.6217
-4.000 -0.3489 0.03188 0.02239 -0.0099 0.8512 0.6309
-3.750 -0.3263 0.03182 0.02218 -0.0091 0.8443 0.6416
-3.500 -0.3034 0.03171 0.02195 -0.0084 0.8380 0.6504
-3.250 -0.2787 0.03172 0.02187 -0.0078 0.8313 0.6583
-3.000 -0.2611 0.03141 0.02144 -0.0070 0.8251 0.6691
-2.750 -0.2336 0.03150 0.02145 -0.0065 0.8196 0.6754
-2.500 -0.2168 0.03124 0.02110 -0.0057 0.8127 0.6855
-2.250 -0.1932 0.03111 0.02091 -0.0051 0.8070 0.6917
-2.000 -0.1691 0.03107 0.02081 -0.0047 0.8014 0.6979
-1.750 -0.1545 0.03079 0.02046 -0.0038 0.7946 0.7077
-1.500 -0.1283 0.03081 0.02044 -0.0033 0.7892 0.7130
-1.250 -0.1052 0.03078 0.02038 -0.0028 0.7829 0.7197
-1.000 -0.0894 0.03059 0.02013 -0.0021 0.7756 0.7286
-0.750 -0.0631 0.03058 0.02011 -0.0016 0.7702 0.7332
-0.500 -0.0411 0.03056 0.02008 -0.0011 0.7640 0.7391
-0.250 -0.0235 0.03048 0.01997 -0.0005 0.7569 0.7461
0.000 0.0000 0.03043 0.01992 0.0000 0.7514 0.7515
0.250 0.0235 0.03048 0.01997 0.0005 0.7461 0.7570
0.500 0.0411 0.03056 0.02008 0.0011 0.7390 0.7640
0.750 0.0631 0.03058 0.02011 0.0016 0.7332 0.7702
1.000 0.0895 0.03059 0.02013 0.0021 0.7286 0.7756
1.250 0.1052 0.03078 0.02038 0.0028 0.7197 0.7829
1.500 0.1283 0.03081 0.02044 0.0033 0.7130 0.7892
1.750 0.1545 0.03079 0.02046 0.0039 0.7077 0.7946
2.000 0.1691 0.03107 0.02081 0.0047 0.6979 0.8014
2.250 0.1932 0.03111 0.02091 0.0051 0.6917 0.8070
2.500 0.2169 0.03123 0.02110 0.0057 0.6855 0.8127
2.750 0.2336 0.03150 0.02145 0.0065 0.6754 0.8197
3.000 0.2611 0.03141 0.02144 0.0070 0.6691 0.8251
3.250 0.2787 0.03172 0.02187 0.0078 0.6584 0.8313
3.500 0.3035 0.03171 0.02195 0.0084 0.6504 0.8381
3.750 0.3263 0.03182 0.02218 0.0091 0.6416 0.8443
4.000 0.3490 0.03188 0.02238 0.0099 0.6309 0.8511
4.250 0.3739 0.03179 0.02240 0.0106 0.6217 0.8587
4.500 0.3978 0.03176 0.02255 0.0114 0.6096 0.8654
4.750 0.4211 0.03172 0.02267 0.0121 0.5973 0.8732
5.000 0.4528 0.03105 0.02215 0.0129 0.5863 0.8803
5.250 0.4776 0.03080 0.02211 0.0137 0.5695 0.8883
5.750 0.5369 0.02949 0.02121 0.0149 0.5334 0.9060
6.000 0.5686 0.02861 0.02052 0.0155 0.5114 0.9160
6.250 0.6004 0.02795 0.02009 0.0154 0.4809 0.9265
6.500 0.6332 0.02726 0.01953 0.0153 0.4402 0.9391
6.750 0.6671 0.02674 0.01892 0.0150 0.3827 0.9549
7.000 0.6922 0.02709 0.01874 0.0149 0.3009 0.9846
7.250 0.6939 0.02833 0.01949 0.0168 0.2471 1.0000
7.500 0.6936 0.02985 0.02063 0.0187 0.2064 1.0000
7.750 0.6950 0.03151 0.02197 0.0202 0.1759 1.0000
8.000 0.6969 0.03322 0.02346 0.0215 0.1528 1.0000
8.250 0.7008 0.03506 0.02507 0.0223 0.1327 1.0000
8.500 0.7061 0.03694 0.02676 0.0230 0.1149 1.0000
8.750 0.7138 0.03872 0.02840 0.0234 0.1004 1.0000
9.000 0.7223 0.04049 0.03006 0.0237 0.0889 1.0000
9.250 0.7321 0.04226 0.03177 0.0242 0.0796 1.0000
9.500 0.7447 0.04392 0.03342 0.0248 0.0727 1.0000
9.750 0.7588 0.04551 0.03500 0.0254 0.0675 1.0000
10.000 0.7724 0.04713 0.03656 0.0258 0.0631 1.0000
10.250 0.7908 0.04865 0.03823 0.0265 0.0593 1.0000
10.500 0.8101 0.05017 0.03974 0.0271 0.0566 1.0000
10.750 0.8313 0.05193 0.04171 0.0278 0.0544 1.0000
11.000 0.8494 0.05380 0.04368 0.0282 0.0528 1.0000
11.250 0.8660 0.05588 0.04582 0.0286 0.0514 1.0000
11.500 0.8745 0.05876 0.04900 0.0287 0.0506 1.0000
11.750 0.8775 0.06198 0.05249 0.0286 0.0499 1.0000
12.000 0.8764 0.06552 0.05627 0.0282 0.0494 1.0000
12.250 0.8701 0.06956 0.06056 0.0274 0.0490 1.0000
12.500 0.8595 0.07412 0.06536 0.0260 0.0489 1.0000
12.750 0.8432 0.07955 0.07103 0.0238 0.0488 1.0000
13.000 0.8205 0.08618 0.07791 0.0204 0.0490 1.0000
13.250 0.7903 0.09468 0.08663 0.0154 0.0494 1.0000
13.500 0.7551 0.10543 0.09758 0.0086 0.0501 1.0000
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