E169 (14.4%) (e169-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E169 (14.4%) (e169-il) Reynolds number: 50,000 Max Cl/Cd: 26.97 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e169-il-50000-n5.txt Download as CSV file: xf-e169-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E169 (14.4%)
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8151 0.10288 0.09544 -0.0045 1.0000 0.0804
-13.750 -0.8538 0.09112 0.08348 -0.0110 1.0000 0.0807
-13.500 -0.8774 0.08308 0.07521 -0.0153 1.0000 0.0822
-13.250 -0.8963 0.07624 0.06810 -0.0187 1.0000 0.0844
-13.000 -0.8970 0.07286 0.06476 -0.0195 1.0000 0.0885
-12.750 -0.9013 0.06901 0.06085 -0.0208 1.0000 0.0929
-12.500 -0.9125 0.06403 0.05563 -0.0228 1.0000 0.0972
-12.250 -0.9120 0.06117 0.05285 -0.0233 1.0000 0.1025
-12.000 -0.9175 0.05746 0.04902 -0.0244 1.0000 0.1085
-11.750 -0.9208 0.05427 0.04583 -0.0250 1.0000 0.1150
-11.500 -0.9253 0.05104 0.04251 -0.0256 1.0000 0.1223
-11.250 -0.9276 0.04834 0.03985 -0.0257 1.0000 0.1300
-11.000 -0.9334 0.04536 0.03673 -0.0257 1.0000 0.1389
-10.750 -0.9351 0.04329 0.03473 -0.0248 1.0000 0.1481
-10.500 -0.9379 0.04131 0.03276 -0.0234 1.0000 0.1582
-10.250 -0.9405 0.03952 0.03094 -0.0215 1.0000 0.1694
-10.000 -0.9385 0.03792 0.02927 -0.0197 1.0000 0.1824
-9.750 -0.9334 0.03658 0.02789 -0.0180 1.0000 0.1965
-9.500 -0.9252 0.03542 0.02670 -0.0163 1.0000 0.2112
-9.250 -0.9145 0.03447 0.02571 -0.0147 1.0000 0.2264
-9.000 -0.9016 0.03365 0.02485 -0.0131 1.0000 0.2417
-8.750 -0.8870 0.03294 0.02408 -0.0116 1.0000 0.2569
-8.500 -0.8710 0.03231 0.02335 -0.0102 1.0000 0.2718
-8.250 -0.8541 0.03171 0.02266 -0.0088 1.0000 0.2863
-8.000 -0.8364 0.03112 0.02196 -0.0075 1.0000 0.3005
-7.750 -0.8183 0.03054 0.02125 -0.0063 1.0000 0.3145
-7.500 -0.7977 0.03014 0.02079 -0.0051 1.0000 0.3273
-7.250 -0.7765 0.02977 0.02036 -0.0039 1.0000 0.3394
-7.000 -0.7558 0.02930 0.01981 -0.0028 1.0000 0.3514
-6.750 -0.7357 0.02873 0.01914 -0.0017 1.0000 0.3636
-6.500 -0.7162 0.02809 0.01836 -0.0006 1.0000 0.3760
-6.250 -0.6939 0.02772 0.01794 0.0004 1.0000 0.3865
-6.000 -0.6723 0.02725 0.01743 0.0015 1.0000 0.3969
-5.750 -0.6521 0.02667 0.01675 0.0025 1.0000 0.4083
-5.500 -0.6313 0.02619 0.01621 0.0036 1.0000 0.4189
-5.250 -0.6098 0.02581 0.01581 0.0047 1.0000 0.4286
-5.000 -0.5902 0.02528 0.01522 0.0059 1.0000 0.4394
-4.750 -0.5705 0.02486 0.01478 0.0070 1.0000 0.4497
-4.500 -0.5508 0.02451 0.01445 0.0083 1.0000 0.4591
-4.250 -0.5337 0.02407 0.01396 0.0096 1.0000 0.4697
-4.000 -0.5173 0.02381 0.01373 0.0112 1.0000 0.4790
-3.750 -0.4848 0.02356 0.01347 0.0096 0.9852 0.4901
-3.500 -0.4406 0.02330 0.01313 0.0060 0.9590 0.5032
-3.250 -0.3961 0.02302 0.01277 0.0025 0.9346 0.5164
-3.000 -0.3524 0.02279 0.01247 -0.0005 0.9111 0.5293
-2.750 -0.3113 0.02261 0.01227 -0.0028 0.8872 0.5409
-2.500 -0.2732 0.02242 0.01202 -0.0044 0.8638 0.5529
-2.250 -0.2400 0.02225 0.01174 -0.0052 0.8402 0.5651
-2.000 -0.2096 0.02211 0.01149 -0.0054 0.8179 0.5777
-1.750 -0.1805 0.02205 0.01138 -0.0051 0.7971 0.5884
-1.500 -0.1537 0.02197 0.01125 -0.0045 0.7766 0.6000
-1.250 -0.1274 0.02190 0.01110 -0.0039 0.7577 0.6124
-1.000 -0.1018 0.02184 0.01096 -0.0032 0.7400 0.6255
-0.750 -0.0761 0.02182 0.01092 -0.0024 0.7234 0.6374
-0.500 -0.0506 0.02180 0.01088 -0.0016 0.7074 0.6501
-0.250 -0.0253 0.02178 0.01084 -0.0008 0.6922 0.6634
0.000 0.0000 0.02178 0.01083 0.0000 0.6775 0.6775
0.250 0.0252 0.02178 0.01084 0.0008 0.6634 0.6922
0.500 0.0506 0.02180 0.01088 0.0016 0.6501 0.7074
0.750 0.0760 0.02182 0.01092 0.0024 0.6374 0.7234
1.000 0.1018 0.02184 0.01096 0.0032 0.6255 0.7400
1.250 0.1274 0.02190 0.01110 0.0039 0.6124 0.7576
1.500 0.1537 0.02197 0.01125 0.0045 0.6001 0.7766
1.750 0.1805 0.02205 0.01138 0.0051 0.5885 0.7971
2.000 0.2096 0.02211 0.01149 0.0054 0.5777 0.8178
2.250 0.2400 0.02225 0.01174 0.0052 0.5651 0.8402
2.500 0.2732 0.02242 0.01202 0.0044 0.5529 0.8638
2.750 0.3113 0.02261 0.01227 0.0028 0.5409 0.8872
3.000 0.3524 0.02279 0.01249 0.0005 0.5293 0.9111
3.250 0.3961 0.02302 0.01277 -0.0025 0.5164 0.9347
3.500 0.4406 0.02330 0.01313 -0.0060 0.5032 0.9590
3.750 0.4848 0.02356 0.01347 -0.0096 0.4902 0.9852
4.000 0.5174 0.02381 0.01373 -0.0112 0.4790 1.0000
4.250 0.5338 0.02407 0.01396 -0.0096 0.4697 1.0000
4.500 0.5509 0.02451 0.01446 -0.0083 0.4591 1.0000
4.750 0.5705 0.02486 0.01478 -0.0071 0.4497 1.0000
5.000 0.5903 0.02528 0.01522 -0.0059 0.4394 1.0000
5.250 0.6098 0.02580 0.01581 -0.0047 0.4286 1.0000
5.500 0.6313 0.02619 0.01621 -0.0036 0.4189 1.0000
5.750 0.6522 0.02667 0.01675 -0.0025 0.4083 1.0000
6.000 0.6723 0.02725 0.01743 -0.0015 0.3969 1.0000
6.250 0.6939 0.02772 0.01794 -0.0004 0.3865 1.0000
6.500 0.7162 0.02809 0.01836 0.0006 0.3759 1.0000
6.750 0.7357 0.02873 0.01914 0.0017 0.3636 1.0000
7.000 0.7558 0.02930 0.01981 0.0028 0.3515 1.0000
7.250 0.7765 0.02977 0.02036 0.0039 0.3395 1.0000
7.500 0.7977 0.03013 0.02078 0.0051 0.3273 1.0000
7.750 0.8182 0.03054 0.02125 0.0063 0.3145 1.0000
8.000 0.8363 0.03113 0.02197 0.0075 0.3005 1.0000
8.250 0.8540 0.03170 0.02264 0.0088 0.2863 1.0000
8.500 0.8710 0.03230 0.02334 0.0102 0.2718 1.0000
8.750 0.8869 0.03294 0.02407 0.0116 0.2569 1.0000
9.000 0.9015 0.03364 0.02484 0.0131 0.2417 1.0000
9.250 0.9144 0.03447 0.02571 0.0147 0.2265 1.0000
9.500 0.9252 0.03542 0.02670 0.0163 0.2113 1.0000
9.750 0.9334 0.03657 0.02788 0.0180 0.1965 1.0000
10.000 0.9385 0.03791 0.02926 0.0197 0.1824 1.0000
10.250 0.9404 0.03951 0.03092 0.0215 0.1694 1.0000
10.500 0.9379 0.04129 0.03275 0.0234 0.1581 1.0000
10.750 0.9352 0.04328 0.03471 0.0248 0.1481 1.0000
11.000 0.9337 0.04534 0.03671 0.0256 0.1389 1.0000
11.250 0.9279 0.04832 0.03982 0.0256 0.1300 1.0000
11.500 0.9256 0.05102 0.04250 0.0256 0.1223 1.0000
11.750 0.9212 0.05424 0.04580 0.0250 0.1150 1.0000
12.000 0.9179 0.05743 0.04899 0.0243 0.1085 1.0000
12.250 0.9126 0.06112 0.05280 0.0233 0.1025 1.0000
12.500 0.9125 0.06406 0.05566 0.0228 0.0971 1.0000
12.750 0.9020 0.06896 0.06080 0.0208 0.0929 1.0000
13.000 0.8980 0.07275 0.06464 0.0195 0.0884 1.0000
13.250 0.8970 0.07620 0.06806 0.0186 0.0844 1.0000
13.500 0.8787 0.08295 0.07508 0.0153 0.0824 1.0000
13.750 0.8549 0.09104 0.08340 0.0111 0.0808 1.0000
14.000 0.8158 0.10289 0.09545 0.0044 0.0805 1.0000
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Polar data table (+)
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