S4053 (s4053-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 200,000 Max Cl/Cd: 75.61 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4053-il-200000-n5.txt Download as CSV file: xf-s4053-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4053
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3933 0.08527 0.08185 -0.0390 1.0000 0.0262
-8.000 -0.3996 0.08203 0.07869 -0.0396 1.0000 0.0262
-7.750 -0.4062 0.07854 0.07525 -0.0409 1.0000 0.0262
-6.750 -0.3889 0.05365 0.05011 -0.0559 0.9880 0.0181
-6.500 -0.3692 0.04667 0.04282 -0.0617 0.9796 0.0182
-6.250 -0.3477 0.04078 0.03657 -0.0658 0.9713 0.0185
-6.000 -0.3228 0.03759 0.03313 -0.0674 0.9626 0.0176
-5.750 -0.2981 0.03289 0.02804 -0.0699 0.9553 0.0171
-5.500 -0.2736 0.02905 0.02375 -0.0710 0.9459 0.0167
-5.250 -0.2469 0.02584 0.02004 -0.0718 0.9372 0.0165
-5.000 -0.2167 0.02308 0.01680 -0.0728 0.9303 0.0163
-4.750 -0.1881 0.02094 0.01424 -0.0731 0.9213 0.0163
-4.500 -0.1560 0.01915 0.01208 -0.0740 0.9145 0.0165
-4.250 -0.1259 0.01774 0.01039 -0.0743 0.9053 0.0169
-4.000 -0.0951 0.01659 0.00902 -0.0748 0.8965 0.0173
-3.750 -0.0637 0.01571 0.00795 -0.0753 0.8879 0.0179
-3.500 -0.0365 0.01452 0.00671 -0.0754 0.8775 0.0200
-3.250 -0.0081 0.01388 0.00600 -0.0754 0.8675 0.0215
-3.000 0.0201 0.01325 0.00526 -0.0754 0.8577 0.0222
-2.750 0.0474 0.01277 0.00465 -0.0751 0.8474 0.0231
-2.500 0.0744 0.01239 0.00413 -0.0748 0.8372 0.0245
-2.250 0.1018 0.01208 0.00369 -0.0745 0.8277 0.0266
-2.000 0.1288 0.01173 0.00329 -0.0742 0.8183 0.0355
-1.750 0.1532 0.01102 0.00303 -0.0737 0.8086 0.1503
-1.500 0.1753 0.01009 0.00293 -0.0731 0.7996 0.3797
-1.250 0.1948 0.00930 0.00293 -0.0715 0.7908 0.6059
-1.000 0.2148 0.00874 0.00298 -0.0690 0.7820 0.7955
-0.750 0.2692 0.00856 0.00288 -0.0738 0.7755 0.9327
-0.500 0.3229 0.00855 0.00275 -0.0792 0.7673 0.9887
-0.250 0.3591 0.00858 0.00264 -0.0810 0.7591 1.0000
0.000 0.3833 0.00865 0.00259 -0.0802 0.7499 1.0000
0.250 0.4076 0.00872 0.00257 -0.0795 0.7410 1.0000
0.500 0.4323 0.00881 0.00255 -0.0788 0.7327 1.0000
0.750 0.4567 0.00889 0.00256 -0.0780 0.7230 1.0000
1.000 0.4813 0.00898 0.00258 -0.0773 0.7136 1.0000
1.250 0.5060 0.00908 0.00259 -0.0766 0.7043 1.0000
1.500 0.5305 0.00917 0.00264 -0.0758 0.6938 1.0000
1.750 0.5551 0.00927 0.00270 -0.0751 0.6835 1.0000
2.000 0.5799 0.00938 0.00276 -0.0744 0.6734 1.0000
2.500 0.6294 0.00960 0.00291 -0.0730 0.6508 1.0000
2.750 0.6540 0.00971 0.00302 -0.0722 0.6380 1.0000
3.000 0.6785 0.00983 0.00311 -0.0715 0.6244 1.0000
3.250 0.7030 0.00996 0.00322 -0.0708 0.6101 1.0000
3.500 0.7274 0.01010 0.00333 -0.0700 0.5946 1.0000
3.750 0.7515 0.01025 0.00346 -0.0692 0.5768 1.0000
4.000 0.7752 0.01042 0.00362 -0.0683 0.5550 1.0000
4.250 0.7984 0.01062 0.00376 -0.0673 0.5297 1.0000
4.500 0.8211 0.01086 0.00393 -0.0662 0.5008 1.0000
4.750 0.8427 0.01118 0.00412 -0.0650 0.4671 1.0000
5.000 0.8638 0.01156 0.00440 -0.0637 0.4289 1.0000
5.250 0.8838 0.01202 0.00470 -0.0623 0.3875 1.0000
5.500 0.9030 0.01258 0.00506 -0.0608 0.3429 1.0000
5.750 0.9217 0.01319 0.00548 -0.0594 0.2983 1.0000
6.000 0.9403 0.01385 0.00594 -0.0580 0.2548 1.0000
6.250 0.9589 0.01452 0.00644 -0.0566 0.2157 1.0000
6.500 0.9780 0.01517 0.00700 -0.0553 0.1827 1.0000
6.750 0.9972 0.01581 0.00755 -0.0540 0.1556 1.0000
7.000 1.0160 0.01647 0.00813 -0.0527 0.1313 1.0000
7.250 1.0344 0.01718 0.00876 -0.0514 0.1096 1.0000
7.500 1.0528 0.01787 0.00941 -0.0500 0.0929 1.0000
7.750 1.0710 0.01856 0.01010 -0.0486 0.0808 1.0000
8.000 1.0885 0.01929 0.01086 -0.0472 0.0710 1.0000
8.250 1.1064 0.01997 0.01161 -0.0457 0.0630 1.0000
8.500 1.1224 0.02077 0.01243 -0.0441 0.0563 1.0000
8.750 1.1391 0.02149 0.01321 -0.0425 0.0500 1.0000
9.000 1.1541 0.02230 0.01405 -0.0408 0.0442 1.0000
9.250 1.1694 0.02301 0.01485 -0.0391 0.0390 1.0000
9.500 1.1801 0.02396 0.01583 -0.0367 0.0349 1.0000
9.750 1.1940 0.02471 0.01674 -0.0348 0.0311 1.0000
10.000 1.2049 0.02568 0.01775 -0.0327 0.0272 1.0000
10.250 1.2140 0.02680 0.01898 -0.0304 0.0244 1.0000
10.500 1.2238 0.02790 0.02022 -0.0283 0.0218 1.0000
10.750 1.2321 0.02914 0.02156 -0.0263 0.0198 1.0000
11.000 1.2338 0.03095 0.02343 -0.0238 0.0180 1.0000
11.250 1.2411 0.03240 0.02505 -0.0219 0.0168 1.0000
11.500 1.2480 0.03390 0.02670 -0.0203 0.0154 1.0000
11.750 1.2549 0.03542 0.02834 -0.0189 0.0141 1.0000
12.000 1.2588 0.03727 0.03032 -0.0174 0.0134 1.0000
12.250 1.2588 0.03955 0.03269 -0.0161 0.0125 1.0000
12.500 1.2575 0.04215 0.03544 -0.0148 0.0121 1.0000
12.750 1.2587 0.04463 0.03816 -0.0139 0.0117 1.0000
13.000 1.2586 0.04732 0.04104 -0.0131 0.0114 1.0000
13.250 1.2567 0.05033 0.04426 -0.0125 0.0109 1.0000
13.500 1.2538 0.05354 0.04767 -0.0123 0.0107 1.0000
13.750 1.2493 0.05707 0.05139 -0.0123 0.0104 1.0000
14.000 1.2438 0.06084 0.05536 -0.0128 0.0101 1.0000
14.250 1.2366 0.06498 0.05970 -0.0136 0.0099 1.0000
14.500 1.2292 0.06932 0.06422 -0.0149 0.0096 1.0000
14.750 1.2190 0.07433 0.06941 -0.0166 0.0094 1.0000
15.000 1.2110 0.07920 0.07444 -0.0188 0.0092 1.0000
15.250 1.1974 0.08541 0.08085 -0.0215 0.0091 1.0000
15.500 1.1858 0.09157 0.08717 -0.0248 0.0090 1.0000
15.750 1.1700 0.09893 0.09473 -0.0287 0.0090 1.0000
16.000 1.1538 0.10683 0.10281 -0.0332 0.0090 1.0000
16.250 1.1357 0.11558 0.11174 -0.0383 0.0090 1.0000
16.500 1.1056 0.12795 0.12438 -0.0456 0.0093 1.0000
16.750 1.0621 0.14528 0.14196 -0.0559 0.0101 1.0000
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Polar data table (+)
Polar graphs
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