S4083 (8%) (s4083-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4083 (8%) (s4083-il) Reynolds number: 50,000 Max Cl/Cd: 31.1 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4083-il-50000.txt Download as CSV file: xf-s4083-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S4083 (8%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3864 0.09992 0.09350 -0.0135 1.0000 0.1933
-7.000 -0.3699 0.09510 0.08871 -0.0120 1.0000 0.2017
-6.750 -0.3875 0.09495 0.08876 -0.0146 1.0000 0.2082
-6.500 -0.3705 0.09013 0.08396 -0.0114 1.0000 0.2190
-6.000 -0.3705 0.08496 0.07901 -0.0130 1.0000 0.2388
-5.750 -0.3691 0.08268 0.07683 -0.0144 1.0000 0.2522
-5.500 -0.3631 0.07961 0.07384 -0.0137 1.0000 0.2667
-5.250 -0.3556 0.07632 0.07062 -0.0118 1.0000 0.2820
-5.000 -0.3469 0.07313 0.06750 -0.0089 1.0000 0.2997
-4.750 -0.3448 0.07091 0.06538 -0.0094 1.0000 0.3248
-4.500 -0.3400 0.06856 0.06309 -0.0076 1.0000 0.3530
-4.000 -0.3287 0.06286 0.05760 0.0018 1.0000 0.4137
-3.750 -0.3239 0.06040 0.05523 0.0064 1.0000 0.4485
-3.000 -0.1356 0.03547 0.02765 -0.0539 1.0000 0.1283
-2.750 -0.1044 0.03219 0.02372 -0.0549 1.0000 0.1187
-2.500 -0.0765 0.02959 0.02064 -0.0551 1.0000 0.1154
-2.250 -0.0500 0.02770 0.01830 -0.0549 1.0000 0.1192
-2.000 -0.0246 0.02600 0.01621 -0.0544 1.0000 0.1251
-1.750 -0.0003 0.02461 0.01465 -0.0537 1.0000 0.1323
-1.500 0.0225 0.02357 0.01343 -0.0528 1.0000 0.1516
-1.250 0.0457 0.02248 0.01245 -0.0522 1.0000 0.1852
-1.000 0.0730 0.02090 0.01148 -0.0523 1.0000 0.3013
-0.750 0.0906 0.01808 0.01067 -0.0494 1.0000 1.0000
-0.500 0.1047 0.01890 0.01102 -0.0491 1.0000 1.0000
-0.250 0.1448 0.01994 0.01158 -0.0538 0.9878 1.0000
0.000 0.2164 0.02075 0.01185 -0.0632 0.9613 1.0000
0.250 0.2817 0.02116 0.01187 -0.0709 0.9347 1.0000
0.500 0.3404 0.02134 0.01180 -0.0769 0.9086 1.0000
0.750 0.3976 0.02135 0.01159 -0.0821 0.8843 1.0000
1.000 0.4586 0.02116 0.01123 -0.0875 0.8635 1.0000
1.250 0.5037 0.02118 0.01113 -0.0901 0.8398 1.0000
1.500 0.5475 0.02121 0.01104 -0.0922 0.8179 1.0000
1.750 0.5860 0.02137 0.01109 -0.0934 0.7962 1.0000
2.000 0.6202 0.02167 0.01130 -0.0939 0.7756 1.0000
2.250 0.6505 0.02211 0.01169 -0.0938 0.7552 1.0000
2.500 0.6822 0.02252 0.01201 -0.0938 0.7371 1.0000
2.750 0.7085 0.02315 0.01261 -0.0932 0.7187 1.0000
3.000 0.7337 0.02385 0.01329 -0.0926 0.7010 1.0000
3.250 0.7594 0.02454 0.01401 -0.0919 0.6844 1.0000
3.500 0.7847 0.02527 0.01473 -0.0911 0.6685 1.0000
3.750 0.8096 0.02603 0.01550 -0.0903 0.6531 1.0000
4.000 0.8339 0.02683 0.01632 -0.0895 0.6379 1.0000
4.250 0.8578 0.02767 0.01720 -0.0885 0.6231 1.0000
4.500 0.8813 0.02855 0.01819 -0.0876 0.6083 1.0000
4.750 0.9043 0.02947 0.01919 -0.0865 0.5937 1.0000
5.000 0.9269 0.03043 0.02024 -0.0855 0.5792 1.0000
5.250 0.9493 0.03142 0.02133 -0.0844 0.5647 1.0000
5.500 0.9715 0.03243 0.02250 -0.0832 0.5500 1.0000
5.750 0.9924 0.03353 0.02373 -0.0820 0.5350 1.0000
6.000 1.0114 0.03476 0.02514 -0.0806 0.5194 1.0000
6.250 1.0302 0.03603 0.02658 -0.0792 0.5035 1.0000
6.500 1.0489 0.03727 0.02801 -0.0777 0.4872 1.0000
6.750 1.0685 0.03841 0.02938 -0.0761 0.4706 1.0000
7.000 1.0898 0.03938 0.03050 -0.0745 0.4538 1.0000
7.250 1.1157 0.03985 0.03107 -0.0730 0.4365 1.0000
7.500 1.1316 0.04121 0.03266 -0.0711 0.4183 1.0000
7.750 1.1483 0.04235 0.03408 -0.0691 0.3988 1.0000
8.000 1.1796 0.04192 0.03367 -0.0674 0.3782 1.0000
8.250 1.1892 0.04364 0.03571 -0.0650 0.3578 1.0000
8.500 1.2172 0.04322 0.03533 -0.0630 0.3343 1.0000
8.750 1.2435 0.04260 0.03471 -0.0608 0.3077 1.0000
9.000 1.2625 0.04238 0.03455 -0.0581 0.2791 1.0000
9.250 1.2763 0.04234 0.03463 -0.0550 0.2477 1.0000
9.500 1.2920 0.04164 0.03359 -0.0518 0.2100 1.0000
9.750 1.2945 0.04292 0.03482 -0.0480 0.1766 1.0000
10.000 1.2994 0.04466 0.03604 -0.0448 0.1438 1.0000
10.250 1.2951 0.04743 0.03904 -0.0413 0.1238 1.0000
10.500 1.3014 0.05019 0.04142 -0.0391 0.1048 1.0000
10.750 1.2973 0.05342 0.04509 -0.0361 0.0958 1.0000
11.000 1.2972 0.05713 0.04900 -0.0339 0.0889 1.0000
11.250 1.2926 0.06082 0.05301 -0.0314 0.0848 1.0000
11.500 1.3048 0.06545 0.05759 -0.0307 0.0799 1.0000
11.750 1.2874 0.06928 0.06179 -0.0281 0.0794 1.0000
12.000 1.2684 0.07351 0.06632 -0.0265 0.0793 1.0000
12.250 1.2478 0.07827 0.07135 -0.0262 0.0793 1.0000
12.500 1.2267 0.08364 0.07694 -0.0272 0.0795 1.0000
12.750 1.2068 0.08958 0.08305 -0.0291 0.0799 1.0000
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Polar data table (+)
Polar graphs
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