USA 5 AIRFOIL (usa5-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 5 AIRFOIL (usa5-il) Reynolds number: 500,000 Max Cl/Cd: 91.89 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa5-il-500000-n5.txt Download as CSV file: xf-usa5-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 5 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3205 0.09716 0.09503 -0.0238 1.0000 0.0076
-8.000 -0.3213 0.09478 0.09269 -0.0233 1.0000 0.0079
-7.750 -0.3215 0.09244 0.09038 -0.0230 0.9997 0.0077
-7.250 -0.2885 0.08478 0.08273 -0.0330 0.9898 0.0090
-7.000 -0.2708 0.08060 0.07856 -0.0383 0.9836 0.0089
-6.750 -0.2440 0.07678 0.07471 -0.0457 0.9783 0.0095
-6.500 -0.2226 0.07269 0.07060 -0.0512 0.9716 0.0096
-6.250 -0.1951 0.06796 0.06585 -0.0582 0.9672 0.0096
-6.000 -0.1793 0.06037 0.05820 -0.0648 0.9591 0.0054
-5.750 -0.1495 0.05557 0.05335 -0.0715 0.9534 0.0052
-5.500 -0.1239 0.05123 0.04893 -0.0764 0.9441 0.0049
-5.250 -0.0965 0.04604 0.04361 -0.0814 0.9343 0.0049
-5.000 -0.0700 0.04101 0.03843 -0.0851 0.9239 0.0050
-4.750 -0.0454 0.03549 0.03269 -0.0877 0.9122 0.0051
-4.500 -0.0250 0.02813 0.02495 -0.0885 0.8992 0.0052
-4.250 -0.0157 0.01671 0.01248 -0.0859 0.8866 0.0054
-4.000 0.0079 0.01498 0.01032 -0.0850 0.8740 0.0058
-3.750 0.0299 0.01283 0.00762 -0.0837 0.8595 0.0063
-3.500 0.0543 0.01172 0.00619 -0.0827 0.8435 0.0066
-3.250 0.0793 0.01100 0.00524 -0.0819 0.8264 0.0071
-3.000 0.1044 0.01042 0.00444 -0.0811 0.8092 0.0079
-2.750 0.1295 0.00995 0.00377 -0.0802 0.7914 0.0090
-2.500 0.1539 0.00957 0.00317 -0.0792 0.7676 0.0107
-2.250 0.1778 0.00921 0.00261 -0.0781 0.7417 0.0144
-2.000 0.2017 0.00905 0.00228 -0.0770 0.7142 0.0196
-1.750 0.2259 0.00893 0.00205 -0.0761 0.6909 0.0317
-1.500 0.2500 0.00885 0.00186 -0.0753 0.6691 0.0415
-1.250 0.2742 0.00880 0.00175 -0.0744 0.6469 0.0561
-1.000 0.2988 0.00885 0.00175 -0.0737 0.6244 0.0756
-0.750 0.3231 0.00894 0.00168 -0.0729 0.5989 0.0829
-0.500 0.3473 0.00905 0.00164 -0.0720 0.5685 0.0891
-0.250 0.3713 0.00919 0.00159 -0.0712 0.5333 0.0928
0.000 0.3947 0.00931 0.00154 -0.0703 0.4961 0.0973
0.250 0.4183 0.00947 0.00153 -0.0694 0.4616 0.1015
0.500 0.4427 0.00962 0.00154 -0.0687 0.4372 0.1056
0.750 0.4672 0.00970 0.00154 -0.0680 0.4187 0.1108
1.000 0.4921 0.00978 0.00156 -0.0675 0.4046 0.1162
1.250 0.5173 0.00986 0.00158 -0.0669 0.3926 0.1195
1.500 0.5424 0.00992 0.00160 -0.0664 0.3831 0.1235
1.750 0.5677 0.00997 0.00165 -0.0659 0.3740 0.1296
2.000 0.5930 0.01002 0.00170 -0.0654 0.3668 0.1393
2.250 0.6180 0.01006 0.00178 -0.0649 0.3589 0.1623
2.500 0.6425 0.01004 0.00189 -0.0643 0.3510 0.2280
3.000 0.7858 0.00895 0.00239 -0.0853 0.3304 1.0000
3.250 0.8107 0.00909 0.00251 -0.0847 0.3249 1.0000
3.500 0.8358 0.00922 0.00264 -0.0842 0.3194 1.0000
3.750 0.8600 0.00941 0.00279 -0.0835 0.3053 1.0000
4.000 0.8840 0.00962 0.00295 -0.0829 0.2883 1.0000
4.250 0.9073 0.00989 0.00311 -0.0821 0.2618 1.0000
4.750 0.9450 0.01133 0.00393 -0.0792 0.1465 1.0000
5.000 0.9565 0.01287 0.00482 -0.0765 0.0187 1.0000
5.250 0.9789 0.01326 0.00527 -0.0755 0.0117 1.0000
5.500 1.0015 0.01361 0.00571 -0.0745 0.0098 1.0000
5.750 1.0235 0.01402 0.00619 -0.0734 0.0078 1.0000
6.000 1.0430 0.01470 0.00703 -0.0719 0.0066 1.0000
6.250 1.0637 0.01523 0.00765 -0.0705 0.0062 1.0000
6.500 1.0836 0.01581 0.00831 -0.0691 0.0055 1.0000
6.750 1.1039 0.01630 0.00883 -0.0679 0.0046 1.0000
7.000 1.1195 0.01725 0.00987 -0.0658 0.0042 1.0000
7.250 1.1342 0.01821 0.01094 -0.0635 0.0040 1.0000
7.500 1.1487 0.01915 0.01198 -0.0612 0.0037 1.0000
7.750 1.1607 0.02022 0.01320 -0.0585 0.0036 1.0000
8.000 1.1709 0.02143 0.01451 -0.0555 0.0035 1.0000
8.250 1.1800 0.02273 0.01591 -0.0524 0.0033 1.0000
8.500 1.1893 0.02409 0.01735 -0.0494 0.0033 1.0000
8.750 1.1988 0.02545 0.01880 -0.0465 0.0031 1.0000
9.000 1.2086 0.02634 0.01975 -0.0438 0.0029 1.0000
9.250 1.2165 0.02721 0.02069 -0.0411 0.0026 1.0000
9.500 1.2222 0.02906 0.02264 -0.0380 0.0025 1.0000
9.750 1.2328 0.03068 0.02443 -0.0355 0.0023 1.0000
10.000 1.2433 0.03279 0.02670 -0.0332 0.0023 1.0000
10.250 1.2524 0.03488 0.02895 -0.0308 0.0023 1.0000
10.500 1.2603 0.03758 0.03190 -0.0282 0.0021 1.0000
10.750 1.2640 0.04019 0.03475 -0.0254 0.0019 1.0000
11.000 1.2636 0.04283 0.03760 -0.0225 0.0019 1.0000
11.250 1.2597 0.04555 0.04054 -0.0197 0.0019 1.0000
11.500 1.2527 0.04853 0.04374 -0.0171 0.0019 1.0000
11.750 1.2440 0.05163 0.04705 -0.0150 0.0019 1.0000
12.000 1.2345 0.05487 0.05048 -0.0135 0.0020 1.0000
12.250 1.2207 0.05886 0.05468 -0.0126 0.0019 1.0000
12.500 1.2060 0.06322 0.05925 -0.0124 0.0019 1.0000
12.750 1.1926 0.06765 0.06385 -0.0130 0.0019 1.0000
13.000 1.1777 0.07265 0.06902 -0.0143 0.0020 1.0000
13.250 1.1603 0.07845 0.07500 -0.0165 0.0019 1.0000
13.500 1.1464 0.08397 0.08066 -0.0190 0.0020 1.0000
13.750 1.1309 0.09021 0.08706 -0.0221 0.0020 1.0000
14.000 1.1138 0.09727 0.09426 -0.0259 0.0020 1.0000
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