NASA SC(2)-1006 AIRFOIL (sc21006-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-1006 AIRFOIL (sc21006-il) Reynolds number: 200,000 Max Cl/Cd: 61.28 at α=-1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc21006-il-200000-n5.txt Download as CSV file: xf-sc21006-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1006 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5134 0.11331 0.10948 -0.0218 0.9999 0.0159
-12.500 -0.5122 0.10977 0.10596 -0.0219 0.9999 0.0153
-12.250 -0.5118 0.10615 0.10238 -0.0225 0.9999 0.0151
-12.000 -0.5124 0.10245 0.09871 -0.0233 0.9999 0.0152
-11.750 -0.5140 0.09864 0.09495 -0.0243 0.9999 0.0156
-10.250 -0.5463 0.07821 0.07485 -0.0250 0.9999 0.0163
-10.000 -0.5502 0.07342 0.07009 -0.0277 0.9999 0.0159
-9.750 -0.5470 0.06701 0.06370 -0.0345 0.9999 0.0156
-9.500 -0.5348 0.05803 0.05460 -0.0455 0.9999 0.0153
-9.250 -0.5148 0.04892 0.04521 -0.0556 0.9999 0.0149
-9.000 -0.4825 0.03971 0.03545 -0.0658 0.9999 0.0146
-8.750 -0.4400 0.03180 0.02676 -0.0748 0.9999 0.0147
-8.500 -0.3975 0.02663 0.02081 -0.0808 0.9999 0.0152
-8.250 -0.3597 0.02360 0.01714 -0.0842 0.9999 0.0158
-8.000 -0.3231 0.02111 0.01416 -0.0873 0.9999 0.0176
-7.750 -0.2889 0.01937 0.01216 -0.0894 0.9999 0.0186
-7.500 -0.2543 0.01794 0.01050 -0.0913 0.9999 0.0192
-7.250 -0.2199 0.01680 0.00920 -0.0930 0.9999 0.0203
-7.000 -0.1855 0.01587 0.00811 -0.0948 0.9999 0.0219
-6.750 -0.1511 0.01511 0.00723 -0.0966 0.9999 0.0243
-6.500 -0.1161 0.01444 0.00646 -0.0986 0.9999 0.0291
-6.250 -0.0837 0.01403 0.00597 -0.0999 0.9999 0.0366
-6.000 -0.0489 0.01351 0.00548 -0.1018 0.9999 0.0544
-5.750 -0.0132 0.01297 0.00514 -0.1041 0.9999 0.1135
-5.500 0.0244 0.01235 0.00495 -0.1070 0.9999 0.2278
-5.250 0.0620 0.01181 0.00495 -0.1099 0.9999 0.3828
-5.000 0.0943 0.01160 0.00501 -0.1112 0.9999 0.4680
-4.750 0.1238 0.01154 0.00506 -0.1117 0.9999 0.5226
-4.500 0.1524 0.01153 0.00516 -0.1120 0.9999 0.5659
-4.250 0.1803 0.01157 0.00528 -0.1121 0.9999 0.6025
-4.000 0.2076 0.01162 0.00544 -0.1120 0.9999 0.6394
-3.750 0.2343 0.01172 0.00561 -0.1118 0.9999 0.6718
-3.500 0.2606 0.01184 0.00580 -0.1115 0.9999 0.6970
-3.250 0.2891 0.01195 0.00597 -0.1117 0.9989 0.7190
-3.000 0.3205 0.01203 0.00612 -0.1125 0.9969 0.7379
-2.750 0.3529 0.01213 0.00628 -0.1136 0.9953 0.7548
-2.500 0.3842 0.01222 0.00644 -0.1144 0.9933 0.7692
-2.250 0.4161 0.01228 0.00658 -0.1153 0.9895 0.7829
-2.000 0.4570 0.01224 0.00664 -0.1180 0.9846 0.7964
-1.750 0.4970 0.01203 0.00658 -0.1203 0.9751 0.8088
-1.500 0.5455 0.01149 0.00619 -0.1241 0.9605 0.8201
-1.000 0.6465 0.01055 0.00376 -0.1290 0.5205 0.8373
-0.750 0.6593 0.01225 0.00434 -0.1262 0.2720 0.8467
-0.500 0.6768 0.01373 0.00492 -0.1246 0.0797 0.8569
-0.250 0.6995 0.01441 0.00543 -0.1235 0.0435 0.8691
0.000 0.7227 0.01487 0.00593 -0.1223 0.0322 0.8827
0.250 0.7453 0.01544 0.00663 -0.1210 0.0273 0.8965
0.500 0.7679 0.01601 0.00733 -0.1196 0.0245 0.9100
0.750 0.7897 0.01669 0.00809 -0.1181 0.0225 0.9247
1.000 0.8096 0.01743 0.00891 -0.1163 0.0208 0.9524
1.250 0.8339 0.01877 0.01031 -0.1155 0.0184 1.0001
1.500 0.8613 0.01982 0.01147 -0.1153 0.0172 1.0001
1.750 0.8886 0.02128 0.01312 -0.1149 0.0163 1.0001
2.000 0.9162 0.02300 0.01505 -0.1145 0.0155 1.0001
2.250 0.9434 0.02503 0.01736 -0.1140 0.0150 1.0001
2.500 0.9696 0.02744 0.02013 -0.1131 0.0147 1.0001
2.750 0.9940 0.03036 0.02351 -0.1119 0.0146 1.0001
3.000 1.0161 0.03370 0.02733 -0.1102 0.0145 1.0001
3.250 1.0371 0.03571 0.02961 -0.1092 0.0133 1.0001
3.500 1.0567 0.03728 0.03139 -0.1083 0.0123 1.0001
3.750 1.0705 0.04088 0.03536 -0.1064 0.0117 1.0001
4.000 1.0793 0.04597 0.04096 -0.1037 0.0115 1.0001
4.250 1.0846 0.05140 0.04686 -0.1007 0.0114 1.0001
4.500 1.0885 0.05660 0.05246 -0.0979 0.0114 1.0001
4.750 1.0919 0.06146 0.05764 -0.0954 0.0115 1.0001
5.000 1.0943 0.06619 0.06266 -0.0930 0.0116 1.0001
5.250 1.0961 0.07115 0.06788 -0.0909 0.0118 1.0001
5.500 1.0774 0.08273 0.07989 -0.0890 0.0135 1.0001
5.750 1.0608 0.08887 0.08618 -0.0882 0.0141 1.0001
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Polar data table (+)
Polar graphs
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