(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: (Dicke 12.28%) (e171-il) Reynolds number: 500,000 Max Cl/Cd: 65.35 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e171-il-500000.txt Download as CSV file: xf-e171-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: (Dicke 12.28%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8400 0.07962 0.07676 -0.0230 1.0000 0.0096
-13.500 -0.8686 0.07111 0.06811 -0.0276 1.0000 0.0094
-13.250 -0.8849 0.06530 0.06214 -0.0310 1.0000 0.0094
-13.000 -0.9058 0.05926 0.05593 -0.0338 1.0000 0.0093
-12.750 -0.9224 0.05429 0.05079 -0.0356 1.0000 0.0093
-12.500 -0.9353 0.05023 0.04654 -0.0366 1.0000 0.0094
-12.250 -0.9491 0.04626 0.04237 -0.0369 1.0000 0.0094
-12.000 -0.9605 0.04275 0.03865 -0.0365 1.0000 0.0093
-11.750 -0.9690 0.03986 0.03554 -0.0354 1.0000 0.0094
-11.500 -0.9663 0.03913 0.03467 -0.0341 1.0000 0.0096
-11.250 -0.9732 0.03679 0.03210 -0.0317 1.0000 0.0097
-11.000 -0.9732 0.03528 0.03044 -0.0292 1.0000 0.0097
-10.750 -0.9794 0.03157 0.02641 -0.0260 1.0000 0.0099
-10.500 -0.9747 0.02911 0.02374 -0.0236 1.0000 0.0099
-10.250 -0.9674 0.02657 0.02100 -0.0214 1.0000 0.0102
-10.000 -0.9570 0.02478 0.01911 -0.0195 1.0000 0.0106
-9.750 -0.9438 0.02353 0.01777 -0.0178 1.0000 0.0108
-9.500 -0.9295 0.02243 0.01659 -0.0161 1.0000 0.0112
-9.250 -0.9139 0.02150 0.01559 -0.0145 1.0000 0.0118
-9.000 -0.8985 0.02047 0.01448 -0.0128 1.0000 0.0124
-8.750 -0.8820 0.01959 0.01350 -0.0112 1.0000 0.0131
-8.500 -0.8648 0.01882 0.01264 -0.0096 1.0000 0.0136
-8.250 -0.8528 0.01756 0.01128 -0.0072 1.0000 0.0144
-8.000 -0.8393 0.01655 0.01025 -0.0051 1.0000 0.0160
-7.750 -0.8210 0.01598 0.00965 -0.0036 1.0000 0.0177
-7.500 -0.8023 0.01546 0.00907 -0.0021 1.0000 0.0191
-7.250 -0.7893 0.01443 0.00797 0.0004 1.0000 0.0217
-7.000 -0.7712 0.01386 0.00737 0.0020 1.0000 0.0246
-6.750 -0.7522 0.01341 0.00687 0.0036 1.0000 0.0273
-6.500 -0.7357 0.01277 0.00625 0.0055 1.0000 0.0339
-6.250 -0.7174 0.01219 0.00572 0.0071 0.9996 0.0453
-6.000 -0.6806 0.01132 0.00508 0.0044 0.9934 0.0855
-5.750 -0.6451 0.01055 0.00456 0.0021 0.9849 0.1358
-5.500 -0.6113 0.00983 0.00410 0.0002 0.9731 0.1934
-5.250 -0.5769 0.00912 0.00367 -0.0018 0.9581 0.2582
-5.000 -0.5424 0.00839 0.00325 -0.0038 0.9394 0.3362
-4.750 -0.5117 0.00783 0.00294 -0.0047 0.9149 0.4129
-4.500 -0.4860 0.00757 0.00278 -0.0042 0.8886 0.4672
-4.250 -0.4610 0.00749 0.00268 -0.0035 0.8658 0.4981
-4.000 -0.4354 0.00747 0.00258 -0.0030 0.8458 0.5195
-3.750 -0.4093 0.00747 0.00248 -0.0025 0.8286 0.5359
-3.500 -0.3832 0.00746 0.00242 -0.0020 0.8133 0.5523
-3.250 -0.3566 0.00746 0.00235 -0.0017 0.7994 0.5659
-3.000 -0.3298 0.00747 0.00229 -0.0014 0.7867 0.5774
-2.750 -0.3029 0.00746 0.00223 -0.0012 0.7750 0.5879
-2.500 -0.2758 0.00746 0.00217 -0.0010 0.7645 0.5979
-2.250 -0.2484 0.00749 0.00212 -0.0008 0.7544 0.6078
-2.000 -0.2211 0.00746 0.00208 -0.0006 0.7445 0.6163
-1.750 -0.1937 0.00747 0.00204 -0.0005 0.7358 0.6252
-1.500 -0.1661 0.00747 0.00201 -0.0004 0.7270 0.6340
-1.250 -0.1385 0.00746 0.00198 -0.0003 0.7188 0.6417
-1.000 -0.1109 0.00749 0.00195 -0.0002 0.7111 0.6500
-0.750 -0.0832 0.00746 0.00195 -0.0002 0.7031 0.6574
-0.250 -0.0278 0.00746 0.00194 0.0000 0.6883 0.6734
0.000 0.0000 0.00749 0.00192 0.0000 0.6813 0.6813
0.250 0.0277 0.00746 0.00194 0.0001 0.6734 0.6883
0.750 0.0832 0.00746 0.00195 0.0002 0.6574 0.7031
1.000 0.1108 0.00749 0.00195 0.0002 0.6500 0.7110
1.250 0.1385 0.00746 0.00199 0.0003 0.6417 0.7188
1.500 0.1661 0.00747 0.00201 0.0004 0.6340 0.7270
1.750 0.1936 0.00747 0.00204 0.0005 0.6252 0.7358
2.000 0.2211 0.00746 0.00208 0.0006 0.6163 0.7445
2.250 0.2484 0.00749 0.00212 0.0008 0.6078 0.7544
2.500 0.2758 0.00746 0.00217 0.0010 0.5979 0.7645
2.750 0.3029 0.00746 0.00223 0.0012 0.5879 0.7751
3.000 0.3298 0.00747 0.00229 0.0014 0.5776 0.7867
3.250 0.3566 0.00746 0.00235 0.0017 0.5660 0.7994
3.500 0.3832 0.00746 0.00242 0.0020 0.5524 0.8133
3.750 0.4093 0.00747 0.00248 0.0025 0.5361 0.8287
4.000 0.4353 0.00747 0.00258 0.0030 0.5196 0.8458
4.250 0.4609 0.00749 0.00268 0.0036 0.4977 0.8658
4.500 0.4860 0.00757 0.00278 0.0042 0.4672 0.8886
4.750 0.5117 0.00783 0.00294 0.0047 0.4127 0.9150
5.000 0.5424 0.00839 0.00325 0.0038 0.3366 0.9395
5.250 0.5771 0.00911 0.00367 0.0018 0.2588 0.9581
5.500 0.6114 0.00983 0.00410 -0.0002 0.1931 0.9731
5.750 0.6452 0.01056 0.00456 -0.0021 0.1347 0.9849
6.000 0.6807 0.01131 0.00508 -0.0044 0.0857 0.9934
6.250 0.7177 0.01219 0.00572 -0.0071 0.0454 0.9996
6.500 0.7356 0.01277 0.00625 -0.0055 0.0339 1.0000
6.750 0.7521 0.01342 0.00687 -0.0036 0.0273 1.0000
7.000 0.7712 0.01387 0.00737 -0.0020 0.0245 1.0000
7.250 0.7893 0.01442 0.00796 -0.0004 0.0217 1.0000
7.500 0.8020 0.01548 0.00908 0.0021 0.0192 1.0000
7.750 0.8212 0.01596 0.00963 0.0035 0.0176 1.0000
8.000 0.8395 0.01654 0.01023 0.0050 0.0159 1.0000
8.250 0.8539 0.01747 0.01118 0.0070 0.0146 1.0000
8.500 0.8647 0.01884 0.01265 0.0096 0.0136 1.0000
8.750 0.8820 0.01962 0.01352 0.0112 0.0131 1.0000
9.000 0.8984 0.02051 0.01452 0.0128 0.0125 1.0000
9.250 0.9142 0.02146 0.01555 0.0144 0.0118 1.0000
9.500 0.9297 0.02242 0.01658 0.0161 0.0112 1.0000
9.750 0.9440 0.02358 0.01783 0.0178 0.0109 1.0000
10.000 0.9568 0.02479 0.01909 0.0195 0.0104 1.0000
10.250 0.9679 0.02648 0.02091 0.0214 0.0102 1.0000
10.500 0.9721 0.03015 0.02485 0.0236 0.0098 1.0000
10.750 0.9791 0.03176 0.02661 0.0260 0.0098 1.0000
11.000 0.9751 0.03504 0.03018 0.0290 0.0098 1.0000
11.250 0.9712 0.03699 0.03233 0.0319 0.0097 1.0000
11.500 0.9688 0.03871 0.03422 0.0340 0.0096 1.0000
11.750 0.9679 0.04005 0.03576 0.0354 0.0094 1.0000
12.000 0.9562 0.04353 0.03946 0.0365 0.0094 1.0000
12.250 0.9527 0.04580 0.04189 0.0368 0.0092 1.0000
12.500 0.9391 0.04974 0.04605 0.0366 0.0092 1.0000
12.750 0.9293 0.05340 0.04987 0.0356 0.0091 1.0000
13.000 0.9060 0.05933 0.05602 0.0336 0.0093 1.0000
13.250 0.8938 0.06403 0.06087 0.0312 0.0092 1.0000
13.500 0.8634 0.07215 0.06916 0.0271 0.0095 1.0000
13.750 0.8548 0.07727 0.07443 0.0235 0.0092 1.0000
14.000 0.8295 0.08610 0.08341 0.0179 0.0094 1.0000
14.250 0.7684 0.10694 0.10460 0.0048 0.0109 1.0000
14.500 0.7617 0.11368 0.11136 0.0009 0.0106 1.0000
14.750 0.7504 0.12185 0.11956 -0.0035 0.0103 1.0000
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Polar data table (+)
Polar graphs
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