WORTMANN FX 71-120 AIRFOIL (fx71120-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 71-120 AIRFOIL (fx71120-il) Reynolds number: 50,000 Max Cl/Cd: 21.16 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx71120-il-50000-n5.txt Download as CSV file: xf-fx71120-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-120 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6448 0.09873 0.08970 -0.0155 1.0000 0.1212
-10.750 -0.6652 0.09038 0.08136 -0.0205 1.0000 0.1211
-10.500 -0.7057 0.07935 0.07028 -0.0280 1.0000 0.1204
-10.250 -0.7549 0.07072 0.06154 -0.0322 1.0000 0.1197
-10.000 -0.7913 0.06545 0.05612 -0.0315 1.0000 0.1194
-9.750 -0.8149 0.06116 0.05163 -0.0298 1.0000 0.1193
-9.500 -0.8291 0.05736 0.04757 -0.0280 1.0000 0.1195
-9.250 -0.8358 0.05400 0.04393 -0.0261 1.0000 0.1197
-9.000 -0.8371 0.05097 0.04060 -0.0241 1.0000 0.1202
-8.750 -0.8350 0.04824 0.03754 -0.0221 1.0000 0.1210
-8.500 -0.8300 0.04576 0.03468 -0.0201 1.0000 0.1220
-8.250 -0.8193 0.04367 0.03235 -0.0184 1.0000 0.1231
-8.000 -0.8028 0.04201 0.03064 -0.0172 1.0000 0.1243
-7.750 -0.7864 0.04041 0.02894 -0.0158 1.0000 0.1255
-7.500 -0.7697 0.03882 0.02722 -0.0144 1.0000 0.1267
-7.250 -0.7523 0.03729 0.02553 -0.0131 1.0000 0.1278
-7.000 -0.7340 0.03584 0.02394 -0.0117 1.0000 0.1291
-6.750 -0.7150 0.03447 0.02243 -0.0104 1.0000 0.1306
-6.500 -0.6952 0.03319 0.02099 -0.0091 1.0000 0.1323
-6.250 -0.6748 0.03199 0.01963 -0.0079 1.0000 0.1342
-6.000 -0.6538 0.03090 0.01839 -0.0067 1.0000 0.1365
-5.750 -0.6325 0.02994 0.01754 -0.0056 1.0000 0.1391
-5.500 -0.6116 0.02908 0.01672 -0.0043 1.0000 0.1425
-5.250 -0.5904 0.02824 0.01585 -0.0031 1.0000 0.1465
-5.000 -0.5685 0.02743 0.01492 -0.0018 1.0000 0.1507
-4.750 -0.5480 0.02662 0.01428 -0.0005 1.0000 0.1548
-4.500 -0.5275 0.02589 0.01359 0.0009 1.0000 0.1603
-4.250 -0.5068 0.02520 0.01288 0.0023 1.0000 0.1670
-4.000 -0.4880 0.02449 0.01231 0.0039 1.0000 0.1750
-3.750 -0.4691 0.02382 0.01174 0.0054 1.0000 0.1862
-3.500 -0.4510 0.02317 0.01125 0.0070 1.0000 0.2020
-3.250 -0.4334 0.02252 0.01079 0.0087 1.0000 0.2235
-3.000 -0.4162 0.02188 0.01037 0.0103 1.0000 0.2546
-2.750 -0.4000 0.02121 0.01004 0.0121 1.0000 0.2971
-2.500 -0.3857 0.02060 0.00982 0.0142 1.0000 0.3523
-2.250 -0.3723 0.02007 0.00972 0.0167 1.0000 0.4193
-2.000 -0.3589 0.01963 0.00974 0.0194 1.0000 0.4926
-1.750 -0.3448 0.01934 0.00987 0.0222 1.0000 0.5672
-1.500 -0.3296 0.01918 0.01010 0.0251 1.0000 0.6421
-1.250 -0.3117 0.01919 0.01046 0.0278 1.0000 0.7165
-1.000 -0.2855 0.01939 0.01093 0.0292 0.9992 0.7887
-0.750 -0.2260 0.01992 0.01157 0.0245 0.9884 0.8543
-0.500 -0.1540 0.02045 0.01210 0.0172 0.9766 0.8960
-0.250 -0.0793 0.02078 0.01239 0.0090 0.9609 0.9238
0.000 0.0001 0.02090 0.01249 0.0000 0.9434 0.9434
0.250 0.0794 0.02078 0.01239 -0.0090 0.9239 0.9609
0.500 0.1540 0.02045 0.01210 -0.0172 0.8961 0.9766
0.750 0.2260 0.01992 0.01157 -0.0245 0.8543 0.9884
1.000 0.2855 0.01939 0.01092 -0.0292 0.7887 0.9992
1.250 0.3116 0.01919 0.01045 -0.0278 0.7162 1.0000
1.500 0.3296 0.01918 0.01010 -0.0251 0.6421 1.0000
1.750 0.3448 0.01933 0.00987 -0.0222 0.5675 1.0000
2.000 0.3588 0.01963 0.00974 -0.0194 0.4923 1.0000
2.250 0.3722 0.02007 0.00972 -0.0167 0.4192 1.0000
2.500 0.3856 0.02061 0.00982 -0.0142 0.3519 1.0000
2.750 0.4000 0.02121 0.01004 -0.0121 0.2969 1.0000
3.000 0.4162 0.02187 0.01037 -0.0103 0.2549 1.0000
3.250 0.4335 0.02251 0.01079 -0.0087 0.2239 1.0000
3.500 0.4510 0.02317 0.01125 -0.0070 0.2023 1.0000
3.750 0.4691 0.02382 0.01174 -0.0054 0.1863 1.0000
4.000 0.4880 0.02449 0.01231 -0.0039 0.1750 1.0000
4.250 0.5068 0.02519 0.01287 -0.0023 0.1671 1.0000
4.500 0.5274 0.02589 0.01359 -0.0009 0.1602 1.0000
4.750 0.5480 0.02663 0.01427 0.0005 0.1548 1.0000
5.000 0.5685 0.02743 0.01492 0.0018 0.1507 1.0000
5.250 0.5904 0.02824 0.01585 0.0031 0.1464 1.0000
5.500 0.6116 0.02908 0.01672 0.0043 0.1424 1.0000
5.750 0.6325 0.02994 0.01754 0.0055 0.1392 1.0000
6.000 0.6538 0.03090 0.01840 0.0067 0.1365 1.0000
6.250 0.6748 0.03199 0.01963 0.0079 0.1342 1.0000
6.500 0.6953 0.03319 0.02099 0.0091 0.1323 1.0000
6.750 0.7150 0.03448 0.02243 0.0104 0.1306 1.0000
7.000 0.7340 0.03584 0.02394 0.0117 0.1291 1.0000
7.250 0.7523 0.03729 0.02553 0.0131 0.1278 1.0000
7.500 0.7697 0.03882 0.02721 0.0144 0.1267 1.0000
7.750 0.7864 0.04041 0.02894 0.0158 0.1255 1.0000
8.000 0.8028 0.04201 0.03065 0.0172 0.1243 1.0000
8.250 0.8193 0.04367 0.03236 0.0184 0.1231 1.0000
8.500 0.8300 0.04576 0.03469 0.0201 0.1220 1.0000
8.750 0.8349 0.04825 0.03755 0.0221 0.1209 1.0000
9.000 0.8373 0.05098 0.04060 0.0241 0.1202 1.0000
9.250 0.8360 0.05400 0.04392 0.0261 0.1198 1.0000
9.500 0.8291 0.05737 0.04758 0.0280 0.1194 1.0000
9.750 0.8152 0.06117 0.05163 0.0298 0.1193 1.0000
10.000 0.7913 0.06547 0.05615 0.0315 0.1194 1.0000
10.250 0.7560 0.07067 0.06149 0.0322 0.1197 1.0000
10.500 0.7061 0.07939 0.07031 0.0279 0.1204 1.0000
10.750 0.6654 0.09048 0.08146 0.0203 0.1211 1.0000
11.000 0.6452 0.09880 0.08978 0.0153 0.1212 1.0000
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