(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: (Dicke 12.28%) (e171-il) Reynolds number: 500,000 Max Cl/Cd: 56.8 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e171-il-500000-n5.txt Download as CSV file: xf-e171-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.8346 0.13333 0.13090 0.0115 1.0000 0.0040
-16.250 -0.8794 0.11706 0.11446 0.0030 1.0000 0.0039
-16.000 -0.9125 0.10458 0.10182 -0.0038 1.0000 0.0038
-15.750 -0.9412 0.09370 0.09078 -0.0100 1.0000 0.0037
-15.500 -0.9630 0.08483 0.08175 -0.0152 1.0000 0.0037
-15.250 -0.9807 0.07727 0.07403 -0.0195 1.0000 0.0037
-15.000 -0.9964 0.07063 0.06724 -0.0232 1.0000 0.0037
-14.750 -1.0122 0.06447 0.06091 -0.0264 1.0000 0.0037
-14.500 -1.0281 0.05878 0.05504 -0.0290 1.0000 0.0037
-14.250 -1.0360 0.05448 0.05059 -0.0308 1.0000 0.0037
-14.000 -1.0444 0.05037 0.04633 -0.0321 1.0000 0.0037
-13.750 -1.0471 0.04714 0.04295 -0.0331 1.0000 0.0038
-13.500 -1.0564 0.04328 0.03890 -0.0337 1.0000 0.0038
-13.250 -1.0592 0.04033 0.03579 -0.0339 1.0000 0.0039
-13.000 -1.0590 0.03783 0.03316 -0.0339 1.0000 0.0040
-12.750 -1.0606 0.03527 0.03044 -0.0335 1.0000 0.0040
-12.500 -1.0589 0.03315 0.02819 -0.0328 1.0000 0.0041
-12.250 -1.0508 0.03175 0.02668 -0.0322 1.0000 0.0043
-12.000 -1.0497 0.02975 0.02454 -0.0309 1.0000 0.0044
-11.750 -1.0465 0.02808 0.02274 -0.0294 1.0000 0.0044
-11.500 -1.0384 0.02691 0.02144 -0.0279 1.0000 0.0046
-11.250 -1.0309 0.02577 0.02020 -0.0262 1.0000 0.0047
-11.000 -1.0305 0.02421 0.01852 -0.0233 1.0000 0.0049
-10.750 -1.0268 0.02302 0.01722 -0.0203 1.0000 0.0052
-10.500 -1.0190 0.02207 0.01619 -0.0177 1.0000 0.0054
-10.250 -1.0068 0.02119 0.01522 -0.0158 1.0000 0.0056
-10.000 -0.9926 0.02037 0.01431 -0.0140 1.0000 0.0058
-9.750 -0.9765 0.01968 0.01356 -0.0125 1.0000 0.0063
-9.500 -0.9606 0.01893 0.01272 -0.0109 1.0000 0.0065
-9.250 -0.9436 0.01825 0.01197 -0.0094 1.0000 0.0071
-9.000 -0.9259 0.01762 0.01126 -0.0080 1.0000 0.0075
-8.750 -0.9075 0.01703 0.01060 -0.0066 1.0000 0.0079
-8.500 -0.8911 0.01627 0.00979 -0.0049 1.0000 0.0088
-8.250 -0.8721 0.01576 0.00925 -0.0036 1.0000 0.0099
-8.000 -0.8521 0.01533 0.00876 -0.0024 1.0000 0.0115
-7.750 -0.8326 0.01487 0.00825 -0.0010 1.0000 0.0128
-7.500 -0.8141 0.01433 0.00770 0.0004 1.0000 0.0146
-7.000 -0.7516 0.01338 0.00666 -0.0019 0.9841 0.0188
-6.750 -0.7194 0.01288 0.00616 -0.0032 0.9664 0.0230
-6.500 -0.6814 0.01235 0.00562 -0.0058 0.9418 0.0320
-6.250 -0.6451 0.01186 0.00513 -0.0080 0.9121 0.0460
-6.000 -0.6191 0.01149 0.00473 -0.0078 0.8802 0.0613
-5.750 -0.5963 0.01115 0.00438 -0.0069 0.8539 0.0820
-5.500 -0.5735 0.01081 0.00405 -0.0061 0.8320 0.1052
-5.000 -0.5266 0.01017 0.00345 -0.0048 0.7978 0.1585
-4.750 -0.5034 0.00977 0.00315 -0.0041 0.7831 0.1983
-4.500 -0.4805 0.00933 0.00286 -0.0034 0.7699 0.2499
-4.250 -0.4579 0.00883 0.00257 -0.0027 0.7576 0.3112
-4.000 -0.4348 0.00839 0.00234 -0.0021 0.7461 0.3729
-3.750 -0.4098 0.00814 0.00216 -0.0016 0.7357 0.4137
-3.500 -0.3846 0.00793 0.00204 -0.0012 0.7261 0.4544
-3.250 -0.3584 0.00781 0.00195 -0.0009 0.7165 0.4817
-3.000 -0.3314 0.00774 0.00187 -0.0007 0.7077 0.5005
-2.500 -0.2771 0.00764 0.00172 -0.0004 0.6912 0.5309
-2.250 -0.2496 0.00761 0.00166 -0.0003 0.6837 0.5433
-2.000 -0.2221 0.00757 0.00162 -0.0002 0.6762 0.5544
-1.750 -0.1946 0.00755 0.00157 -0.0002 0.6693 0.5649
-1.500 -0.1669 0.00753 0.00153 -0.0001 0.6621 0.5745
-1.250 -0.1392 0.00752 0.00150 -0.0001 0.6557 0.5836
-1.000 -0.1114 0.00750 0.00147 -0.0001 0.6488 0.5916
-0.500 -0.0557 0.00748 0.00144 0.0000 0.6361 0.6082
-0.250 -0.0279 0.00748 0.00143 0.0000 0.6297 0.6160
0.000 0.0000 0.00747 0.00143 0.0000 0.6232 0.6231
0.250 0.0279 0.00748 0.00143 0.0000 0.6160 0.6297
0.500 0.0557 0.00748 0.00144 0.0000 0.6082 0.6361
1.000 0.1113 0.00750 0.00147 0.0001 0.5916 0.6488
1.250 0.1392 0.00752 0.00150 0.0001 0.5836 0.6557
1.500 0.1669 0.00753 0.00153 0.0001 0.5745 0.6621
1.750 0.1946 0.00755 0.00157 0.0002 0.5649 0.6693
2.000 0.2221 0.00757 0.00162 0.0002 0.5544 0.6762
2.500 0.2771 0.00764 0.00172 0.0004 0.5309 0.6912
3.000 0.3314 0.00774 0.00187 0.0007 0.5004 0.7077
3.250 0.3584 0.00781 0.00195 0.0009 0.4817 0.7165
3.500 0.3847 0.00793 0.00204 0.0012 0.4546 0.7261
3.750 0.4098 0.00814 0.00216 0.0016 0.4136 0.7357
4.000 0.4348 0.00839 0.00234 0.0020 0.3732 0.7462
4.250 0.4582 0.00881 0.00257 0.0027 0.3138 0.7577
4.500 0.4808 0.00930 0.00285 0.0034 0.2527 0.7699
4.750 0.5036 0.00977 0.00315 0.0041 0.1985 0.7831
5.000 0.5268 0.01017 0.00345 0.0047 0.1585 0.7978
5.250 0.5504 0.01050 0.00373 0.0054 0.1297 0.8139
5.500 0.5737 0.01081 0.00405 0.0061 0.1052 0.8319
5.750 0.5965 0.01115 0.00438 0.0069 0.0820 0.8538
6.000 0.6194 0.01149 0.00473 0.0077 0.0616 0.8800
6.250 0.6452 0.01186 0.00513 0.0080 0.0458 0.9119
6.500 0.6815 0.01235 0.00562 0.0058 0.0317 0.9419
6.750 0.7195 0.01288 0.00616 0.0032 0.0231 0.9665
7.000 0.7519 0.01338 0.00666 0.0018 0.0188 0.9843
7.500 0.8139 0.01433 0.00770 -0.0004 0.0146 1.0000
7.750 0.8322 0.01490 0.00828 0.0011 0.0126 1.0000
8.000 0.8522 0.01532 0.00875 0.0024 0.0115 1.0000
8.250 0.8721 0.01575 0.00925 0.0036 0.0100 1.0000
8.500 0.8912 0.01627 0.00979 0.0049 0.0088 1.0000
8.750 0.9078 0.01702 0.01058 0.0065 0.0079 1.0000
9.000 0.9264 0.01760 0.01124 0.0079 0.0074 1.0000
9.250 0.9440 0.01825 0.01197 0.0094 0.0070 1.0000
9.500 0.9610 0.01894 0.01273 0.0108 0.0066 1.0000
9.750 0.9772 0.01966 0.01353 0.0124 0.0062 1.0000
10.000 0.9923 0.02045 0.01440 0.0140 0.0060 1.0000
10.250 1.0076 0.02118 0.01522 0.0156 0.0056 1.0000
10.500 1.0198 0.02208 0.01620 0.0175 0.0053 1.0000
10.750 1.0279 0.02302 0.01723 0.0201 0.0052 1.0000
11.000 1.0315 0.02423 0.01853 0.0231 0.0049 1.0000
11.250 1.0300 0.02592 0.02037 0.0262 0.0047 1.0000
11.500 1.0364 0.02717 0.02173 0.0280 0.0046 1.0000
11.750 1.0432 0.02846 0.02312 0.0295 0.0045 1.0000
12.000 1.0497 0.02987 0.02467 0.0308 0.0044 1.0000
12.250 1.0560 0.03137 0.02628 0.0318 0.0042 1.0000
12.500 1.0557 0.03359 0.02866 0.0328 0.0042 1.0000
12.750 1.0599 0.03547 0.03066 0.0333 0.0041 1.0000
13.000 1.0591 0.03798 0.03332 0.0337 0.0040 1.0000
13.250 1.0563 0.04082 0.03632 0.0338 0.0039 1.0000
13.500 1.0574 0.04333 0.03895 0.0335 0.0038 1.0000
13.750 1.0524 0.04668 0.04248 0.0329 0.0038 1.0000
14.000 1.0441 0.05061 0.04658 0.0319 0.0038 1.0000
14.250 1.0358 0.05475 0.05088 0.0304 0.0037 1.0000
14.500 1.0253 0.05941 0.05570 0.0285 0.0037 1.0000
14.750 1.0116 0.06481 0.06126 0.0260 0.0037 1.0000
15.000 0.9965 0.07091 0.06753 0.0228 0.0037 1.0000
15.250 0.9801 0.07773 0.07451 0.0190 0.0037 1.0000
15.500 0.9615 0.08549 0.08243 0.0145 0.0037 1.0000
15.750 0.9355 0.09527 0.09239 0.0088 0.0038 1.0000
16.000 0.9178 0.10387 0.10109 0.0039 0.0037 1.0000
16.250 0.8819 0.11698 0.11438 -0.0033 0.0038 1.0000
16.500 0.8362 0.13340 0.13096 -0.0118 0.0041 1.0000
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Polar data table (+)
Polar graphs
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