NASA SC(2)-0706 AIRFOIL (sc20706-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0706 AIRFOIL (sc20706-il) Reynolds number: 1,000,000 Max Cl/Cd: 68.03 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20706-il-1000000-n5.txt Download as CSV file: xf-sc20706-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0706 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6400 0.08436 0.08274 -0.0161 1.0000 0.0045
-10.000 -0.6517 0.07921 0.07762 -0.0178 1.0000 0.0046
-9.750 -0.6726 0.07419 0.07266 -0.0183 1.0000 0.0046
-9.500 -0.6933 0.06254 0.06099 -0.0318 1.0000 0.0045
-9.250 -0.7016 0.02491 0.02179 -0.0608 0.9977 0.0052
-9.000 -0.6722 0.02078 0.01715 -0.0640 0.9976 0.0055
-8.750 -0.6421 0.01835 0.01436 -0.0660 0.9974 0.0057
-8.500 -0.6119 0.01655 0.01228 -0.0676 0.9973 0.0059
-8.250 -0.5818 0.01536 0.01090 -0.0689 0.9971 0.0060
-8.000 -0.5520 0.01457 0.00997 -0.0699 0.9969 0.0062
-7.750 -0.5218 0.01367 0.00891 -0.0710 0.9967 0.0064
-7.500 -0.4913 0.01280 0.00790 -0.0721 0.9965 0.0065
-7.250 -0.4592 0.01143 0.00632 -0.0737 0.9967 0.0069
-7.000 -0.4279 0.01069 0.00549 -0.0749 0.9966 0.0075
-6.750 -0.3973 0.01028 0.00504 -0.0758 0.9964 0.0080
-6.500 -0.3668 0.00995 0.00464 -0.0767 0.9962 0.0085
-6.250 -0.3362 0.00961 0.00426 -0.0776 0.9960 0.0090
-6.000 -0.3055 0.00930 0.00390 -0.0785 0.9958 0.0095
-5.750 -0.2748 0.00902 0.00358 -0.0794 0.9957 0.0099
-5.500 -0.2440 0.00879 0.00331 -0.0802 0.9954 0.0105
-5.250 -0.2127 0.00851 0.00300 -0.0812 0.9953 0.0127
-5.000 -0.1817 0.00832 0.00282 -0.0820 0.9951 0.0159
-4.750 -0.1511 0.00817 0.00266 -0.0828 0.9949 0.0187
-4.500 -0.1203 0.00800 0.00252 -0.0836 0.9947 0.0238
-4.250 -0.0898 0.00789 0.00241 -0.0844 0.9945 0.0276
-4.000 -0.0596 0.00775 0.00230 -0.0850 0.9942 0.0372
-3.750 -0.0290 0.00754 0.00221 -0.0859 0.9940 0.0646
-3.500 0.0024 0.00731 0.00213 -0.0869 0.9937 0.1065
-3.250 0.0348 0.00705 0.00205 -0.0882 0.9933 0.1601
-3.000 0.0696 0.00673 0.00194 -0.0900 0.9921 0.2259
-2.750 0.1107 0.00609 0.00179 -0.0936 0.9905 0.3743
-2.500 0.1565 0.00546 0.00161 -0.0980 0.9871 0.5183
-2.250 0.2017 0.00512 0.00142 -0.1020 0.9838 0.5686
-2.000 0.2325 0.00498 0.00138 -0.1026 0.9793 0.5988
-1.750 0.2704 0.00480 0.00125 -0.1048 0.9734 0.6157
-1.500 0.3043 0.00468 0.00120 -0.1061 0.9648 0.6310
-1.250 0.3340 0.00585 0.00109 -0.1060 0.6292 0.6442
-1.000 0.3578 0.00664 0.00126 -0.1054 0.4538 0.6558
-0.750 0.3827 0.00737 0.00143 -0.1050 0.2909 0.6656
-0.500 0.4091 0.00787 0.00157 -0.1049 0.1833 0.6749
-0.250 0.4362 0.00820 0.00172 -0.1048 0.1195 0.6839
0.000 0.4634 0.00853 0.00186 -0.1048 0.0671 0.6923
0.250 0.4909 0.00878 0.00201 -0.1047 0.0381 0.6999
0.500 0.5187 0.00895 0.00215 -0.1047 0.0286 0.7065
0.750 0.5465 0.00911 0.00233 -0.1046 0.0237 0.7131
1.000 0.5743 0.00927 0.00250 -0.1046 0.0199 0.7196
1.250 0.6018 0.00948 0.00271 -0.1045 0.0153 0.7266
1.500 0.6294 0.00967 0.00291 -0.1044 0.0129 0.7327
1.750 0.6567 0.00994 0.00319 -0.1042 0.0105 0.7390
2.000 0.6837 0.01030 0.00364 -0.1039 0.0094 0.7447
2.250 0.7109 0.01056 0.00394 -0.1037 0.0091 0.7506
2.500 0.7379 0.01087 0.00430 -0.1035 0.0087 0.7562
2.750 0.7647 0.01124 0.00474 -0.1032 0.0084 0.7620
3.000 0.7913 0.01165 0.00522 -0.1028 0.0081 0.7683
3.250 0.8177 0.01208 0.00574 -0.1025 0.0078 0.7736
3.500 0.8439 0.01253 0.00627 -0.1021 0.0075 0.7794
3.750 0.8701 0.01298 0.00678 -0.1017 0.0072 0.7848
4.000 0.8962 0.01344 0.00732 -0.1013 0.0068 0.7902
4.250 0.9220 0.01401 0.00796 -0.1008 0.0065 0.7956
4.500 0.9461 0.01513 0.00925 -0.1000 0.0060 0.8006
4.750 0.9685 0.01709 0.01154 -0.0987 0.0057 0.8061
5.000 0.9938 0.01786 0.01244 -0.0982 0.0056 0.8115
5.250 1.0187 0.01860 0.01333 -0.0976 0.0055 0.8160
5.500 1.0428 0.01968 0.01459 -0.0969 0.0053 0.8209
5.750 1.0651 0.02138 0.01657 -0.0958 0.0052 0.8254
6.000 1.0857 0.02352 0.01905 -0.0944 0.0050 0.8299
6.250 1.1023 0.02695 0.02296 -0.0923 0.0048 0.8348
6.500 1.0623 0.05185 0.04946 -0.0818 0.0041 0.8374
6.750 1.0607 0.05995 0.05789 -0.0796 0.0039 0.8417
7.000 1.0585 0.06714 0.06530 -0.0785 0.0037 0.8467
7.250 1.0528 0.07442 0.07277 -0.0784 0.0037 0.8517
7.500 1.0431 0.08167 0.08017 -0.0793 0.0036 0.8565
7.750 1.0283 0.08917 0.08778 -0.0816 0.0036 0.8622
8.000 1.0055 0.09601 0.09468 -0.0844 0.0037 0.8689
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Polar data table (+)
Polar graphs
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