NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.1 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20710-il-1000000-n5.txt Download as CSV file: xf-sc20710-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0710 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
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0358 0.09589 0.09331 -0.0376 1.0000 0.0104
-17.750 -1.0994 0.07908 0.07624 -0.0473 1.0000 0.0102
-17.500 -1.1354 0.06780 0.06475 -0.0544 1.0000 0.0102
-17.250 -1.1585 0.05960 0.05637 -0.0598 1.0000 0.0102
-17.000 -1.1749 0.05330 0.04992 -0.0637 1.0000 0.0102
-16.750 -1.1869 0.04836 0.04484 -0.0664 1.0000 0.0102
-16.500 -1.1951 0.04434 0.04070 -0.0681 1.0000 0.0103
-16.250 -1.2006 0.04098 0.03723 -0.0692 1.0000 0.0104
-16.000 -1.2035 0.03818 0.03432 -0.0696 1.0000 0.0104
-15.750 -1.2045 0.03582 0.03187 -0.0696 1.0000 0.0105
-15.500 -1.2046 0.03379 0.02976 -0.0690 1.0000 0.0106
-15.250 -1.2041 0.03202 0.02791 -0.0680 1.0000 0.0107
-15.000 -1.2044 0.03048 0.02629 -0.0663 1.0000 0.0108
-14.750 -1.2081 0.02916 0.02490 -0.0637 1.0000 0.0109
-14.500 -1.2142 0.02796 0.02364 -0.0603 1.0000 0.0109
-14.250 -1.2091 0.02672 0.02232 -0.0589 1.0000 0.0110
-14.000 -1.1905 0.02538 0.02089 -0.0600 0.9993 0.0111
-13.750 -1.1654 0.02411 0.01952 -0.0621 0.9983 0.0113
-13.500 -1.1391 0.02293 0.01826 -0.0643 0.9973 0.0114
-13.250 -1.1116 0.02186 0.01709 -0.0664 0.9964 0.0116
-13.000 -1.0833 0.02088 0.01601 -0.0684 0.9956 0.0118
-12.750 -1.0545 0.01999 0.01504 -0.0702 0.9949 0.0119
-12.500 -1.0252 0.01918 0.01415 -0.0720 0.9943 0.0121
-12.250 -0.9963 0.01843 0.01332 -0.0735 0.9936 0.0123
-12.000 -0.9684 0.01775 0.01257 -0.0746 0.9925 0.0124
-11.750 -0.9395 0.01712 0.01187 -0.0759 0.9913 0.0126
-11.500 -0.9102 0.01649 0.01119 -0.0772 0.9903 0.0127
-11.250 -0.8803 0.01574 0.01037 -0.0787 0.9894 0.0131
-11.000 -0.8500 0.01514 0.00973 -0.0801 0.9885 0.0135
-10.750 -0.8193 0.01462 0.00919 -0.0815 0.9877 0.0139
-10.500 -0.7882 0.01415 0.00869 -0.0829 0.9870 0.0143
-10.250 -0.7569 0.01372 0.00822 -0.0843 0.9864 0.0148
-10.000 -0.7252 0.01329 0.00776 -0.0857 0.9858 0.0152
-9.750 -0.6932 0.01289 0.00732 -0.0871 0.9853 0.0156
-9.500 -0.6611 0.01250 0.00690 -0.0886 0.9849 0.0161
-9.250 -0.6286 0.01208 0.00647 -0.0901 0.9845 0.0170
-9.000 -0.5961 0.01173 0.00612 -0.0916 0.9841 0.0180
-8.750 -0.5633 0.01141 0.00578 -0.0931 0.9837 0.0191
-8.500 -0.5333 0.01111 0.00547 -0.0940 0.9824 0.0204
-8.250 -0.5034 0.01082 0.00520 -0.0948 0.9807 0.0222
-8.000 -0.4722 0.01057 0.00494 -0.0958 0.9794 0.0238
-7.750 -0.4402 0.01029 0.00468 -0.0971 0.9783 0.0259
-7.500 -0.4078 0.01005 0.00444 -0.0984 0.9774 0.0280
-7.250 -0.3753 0.00983 0.00422 -0.0997 0.9765 0.0297
-7.000 -0.3423 0.00957 0.00398 -0.1011 0.9757 0.0322
-6.750 -0.3096 0.00935 0.00377 -0.1024 0.9748 0.0343
-6.500 -0.2769 0.00915 0.00357 -0.1037 0.9740 0.0359
-6.250 -0.2440 0.00893 0.00337 -0.1050 0.9733 0.0390
-6.000 -0.2112 0.00873 0.00319 -0.1063 0.9726 0.0422
-5.750 -0.1782 0.00852 0.00302 -0.1076 0.9720 0.0478
-5.500 -0.1463 0.00833 0.00287 -0.1087 0.9708 0.0544
-5.250 -0.1158 0.00815 0.00274 -0.1095 0.9687 0.0615
-5.000 -0.0843 0.00797 0.00261 -0.1104 0.9670 0.0711
-4.750 -0.0524 0.00779 0.00248 -0.1115 0.9654 0.0821
-4.500 -0.0200 0.00759 0.00236 -0.1126 0.9640 0.0991
-4.250 0.0124 0.00740 0.00224 -0.1138 0.9627 0.1158
-4.000 0.0461 0.00714 0.00212 -0.1154 0.9615 0.1514
-3.750 0.0806 0.00684 0.00199 -0.1171 0.9601 0.1963
-3.500 0.1161 0.00651 0.00185 -0.1191 0.9582 0.2527
-3.250 0.1490 0.00615 0.00174 -0.1205 0.9532 0.3228
-3.000 0.1851 0.00566 0.00159 -0.1228 0.9487 0.4237
-2.750 0.2214 0.00522 0.00146 -0.1249 0.9414 0.5258
-2.500 0.2521 0.00509 0.00140 -0.1254 0.9270 0.5663
-2.250 0.2818 0.00504 0.00140 -0.1256 0.9132 0.5948
-2.000 0.3109 0.00505 0.00140 -0.1256 0.8965 0.6164
-1.750 0.3388 0.00512 0.00139 -0.1254 0.8683 0.6261
-1.500 0.3650 0.00533 0.00137 -0.1247 0.8098 0.6309
-1.250 0.3816 0.00658 0.00161 -0.1223 0.5725 0.6342
-1.000 0.4051 0.00737 0.00182 -0.1215 0.4238 0.6387
-0.750 0.4307 0.00793 0.00198 -0.1212 0.3208 0.6455
-0.500 0.4575 0.00832 0.00213 -0.1210 0.2531 0.6521
-0.250 0.4847 0.00867 0.00228 -0.1209 0.1984 0.6588
0.000 0.5121 0.00897 0.00241 -0.1208 0.1554 0.6645
0.250 0.5395 0.00925 0.00257 -0.1207 0.1202 0.6690
0.500 0.5672 0.00950 0.00270 -0.1206 0.0960 0.6717
0.750 0.5952 0.00970 0.00283 -0.1206 0.0806 0.6739
1.000 0.6232 0.00990 0.00296 -0.1206 0.0688 0.6761
1.500 0.6790 0.01026 0.00326 -0.1204 0.0533 0.6806
1.750 0.7068 0.01046 0.00342 -0.1203 0.0468 0.6828
2.000 0.7345 0.01066 0.00359 -0.1202 0.0420 0.6849
2.250 0.7622 0.01085 0.00377 -0.1201 0.0385 0.6871
2.500 0.7899 0.01105 0.00395 -0.1200 0.0360 0.6896
2.750 0.8173 0.01127 0.00415 -0.1198 0.0334 0.6920
3.000 0.8449 0.01147 0.00435 -0.1197 0.0318 0.6941
3.250 0.8724 0.01167 0.00456 -0.1195 0.0302 0.6960
3.500 0.8996 0.01190 0.00478 -0.1193 0.0283 0.6980
3.750 0.9266 0.01215 0.00504 -0.1191 0.0264 0.7001
4.000 0.9538 0.01236 0.00527 -0.1188 0.0250 0.7022
4.250 0.9807 0.01261 0.00551 -0.1186 0.0230 0.7044
4.500 1.0074 0.01289 0.00578 -0.1183 0.0213 0.7066
4.750 1.0341 0.01315 0.00605 -0.1180 0.0197 0.7087
5.000 1.0605 0.01346 0.00634 -0.1176 0.0182 0.7107
5.250 1.0867 0.01376 0.00668 -0.1172 0.0173 0.7128
5.500 1.1129 0.01407 0.00702 -0.1168 0.0166 0.7150
5.750 1.1389 0.01440 0.00737 -0.1164 0.0158 0.7174
6.000 1.1646 0.01476 0.00774 -0.1159 0.0152 0.7199
6.250 1.1900 0.01516 0.00816 -0.1153 0.0146 0.7222
6.500 1.2152 0.01559 0.00862 -0.1148 0.0141 0.7243
6.750 1.2405 0.01597 0.00904 -0.1142 0.0139 0.7261
7.000 1.2655 0.01637 0.00950 -0.1136 0.0136 0.7280
7.250 1.2903 0.01679 0.00998 -0.1130 0.0134 0.7300
7.500 1.3148 0.01724 0.01048 -0.1123 0.0131 0.7320
7.750 1.3390 0.01770 0.01099 -0.1115 0.0129 0.7341
8.000 1.3630 0.01818 0.01152 -0.1108 0.0126 0.7363
8.250 1.3867 0.01867 0.01207 -0.1100 0.0124 0.7384
8.500 1.4102 0.01919 0.01262 -0.1092 0.0121 0.7404
8.750 1.4331 0.01975 0.01323 -0.1083 0.0118 0.7422
9.000 1.4553 0.02039 0.01393 -0.1072 0.0116 0.7441
9.250 1.4763 0.02114 0.01478 -0.1060 0.0113 0.7460
9.500 1.4966 0.02196 0.01568 -0.1047 0.0111 0.7481
9.750 1.5179 0.02259 0.01640 -0.1035 0.0111 0.7504
10.000 1.5386 0.02325 0.01715 -0.1023 0.0110 0.7527
10.250 1.5586 0.02396 0.01795 -0.1009 0.0109 0.7548
10.500 1.5780 0.02471 0.01880 -0.0995 0.0108 0.7569
10.750 1.5966 0.02549 0.01967 -0.0980 0.0107 0.7588
11.000 1.6142 0.02632 0.02061 -0.0963 0.0106 0.7609
11.250 1.6308 0.02719 0.02160 -0.0945 0.0105 0.7631
11.500 1.6463 0.02811 0.02263 -0.0925 0.0104 0.7653
11.750 1.6604 0.02909 0.02372 -0.0903 0.0103 0.7676
12.000 1.6730 0.03009 0.02484 -0.0879 0.0101 0.7699
12.250 1.6828 0.03116 0.02602 -0.0851 0.0101 0.7720
12.500 1.6892 0.03224 0.02722 -0.0817 0.0100 0.7739
12.750 1.6930 0.03338 0.02848 -0.0780 0.0099 0.7758
13.000 1.6968 0.03470 0.02992 -0.0746 0.0098 0.7777
13.250 1.7000 0.03611 0.03146 -0.0713 0.0098 0.7797
13.500 1.7014 0.03770 0.03319 -0.0680 0.0097 0.7818
13.750 1.7023 0.03941 0.03503 -0.0650 0.0096 0.7840
14.000 1.7014 0.04134 0.03708 -0.0620 0.0096 0.7862
14.250 1.7001 0.04339 0.03926 -0.0594 0.0095 0.7882
14.750 1.6913 0.04845 0.04459 -0.0549 0.0094 0.7917
15.000 1.6840 0.05153 0.04781 -0.0533 0.0093 0.7935
15.250 1.6735 0.05525 0.05169 -0.0523 0.0093 0.7952
15.500 1.6582 0.06002 0.05662 -0.0523 0.0092 0.7969
15.750 1.6384 0.06607 0.06286 -0.0538 0.0092 0.7985
16.000 1.6108 0.07464 0.07164 -0.0581 0.0092 0.7999
16.250 1.5592 0.09045 0.08777 -0.0689 0.0093 0.8004
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0710 AIRFOIL (sc20710-il)