NASA SC(2)-0606 AIRFOIL (sc20606-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0606 AIRFOIL (sc20606-il) Reynolds number: 1,000,000 Max Cl/Cd: 65.63 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20606-il-1000000-n5.txt Download as CSV file: xf-sc20606-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0606 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6636 0.08106 0.07945 -0.0137 1.0000 0.0046
-9.750 -0.6755 0.07418 0.07261 -0.0183 1.0000 0.0046
-9.500 -0.6959 0.06157 0.05997 -0.0336 1.0000 0.0045
-9.250 -0.7447 0.02779 0.02491 -0.0509 1.0000 0.0050
-9.000 -0.7219 0.02262 0.01918 -0.0533 1.0000 0.0052
-8.750 -0.6958 0.01992 0.01611 -0.0547 1.0000 0.0054
-8.500 -0.6688 0.01791 0.01380 -0.0557 1.0000 0.0056
-8.250 -0.6415 0.01643 0.01210 -0.0565 1.0000 0.0057
-8.000 -0.6146 0.01552 0.01104 -0.0569 1.0000 0.0059
-7.750 -0.5877 0.01477 0.01017 -0.0572 1.0000 0.0061
-7.500 -0.5602 0.01386 0.00909 -0.0576 1.0000 0.0062
-7.250 -0.5311 0.01256 0.00760 -0.0584 1.0000 0.0064
-7.000 -0.5004 0.01122 0.00606 -0.0597 1.0000 0.0070
-6.750 -0.4725 0.01070 0.00549 -0.0601 1.0000 0.0075
-6.500 -0.4448 0.01031 0.00505 -0.0603 1.0000 0.0079
-6.250 -0.4170 0.00993 0.00460 -0.0606 1.0000 0.0082
-6.000 -0.3890 0.00956 0.00419 -0.0609 1.0000 0.0086
-5.750 -0.3609 0.00923 0.00380 -0.0611 1.0000 0.0090
-5.500 -0.3328 0.00893 0.00346 -0.0614 1.0000 0.0093
-5.250 -0.3049 0.00867 0.00316 -0.0616 1.0000 0.0097
-5.000 -0.2770 0.00848 0.00293 -0.0618 0.9999 0.0102
-4.750 -0.2452 0.00819 0.00259 -0.0628 0.9995 0.0114
-4.500 -0.2135 0.00795 0.00236 -0.0638 0.9991 0.0150
-4.250 -0.1817 0.00773 0.00219 -0.0648 0.9985 0.0224
-4.000 -0.1497 0.00757 0.00205 -0.0659 0.9978 0.0302
-3.750 -0.1174 0.00741 0.00191 -0.0670 0.9971 0.0384
-3.500 -0.0852 0.00723 0.00180 -0.0681 0.9964 0.0532
-3.250 -0.0525 0.00691 0.00169 -0.0695 0.9959 0.1048
-3.000 -0.0186 0.00657 0.00159 -0.0712 0.9954 0.1715
-2.750 0.0175 0.00625 0.00147 -0.0733 0.9945 0.2368
-2.500 0.0535 0.00588 0.00134 -0.0754 0.9922 0.3149
-2.250 0.0932 0.00530 0.00121 -0.0785 0.9888 0.4505
-2.000 0.1355 0.00485 0.00112 -0.0820 0.9846 0.5641
-1.750 0.1690 0.00473 0.00107 -0.0833 0.9783 0.5894
-1.500 0.2046 0.00458 0.00101 -0.0850 0.9672 0.6158
-1.250 0.2422 0.00449 0.00093 -0.0870 0.9423 0.6310
-1.000 0.2691 0.00466 0.00091 -0.0864 0.8643 0.6451
-0.750 0.2868 0.00611 0.00109 -0.0842 0.5406 0.6580
-0.500 0.3124 0.00683 0.00123 -0.0841 0.3735 0.6725
-0.250 0.3397 0.00719 0.00135 -0.0841 0.2890 0.6867
0.000 0.3669 0.00756 0.00148 -0.0841 0.2093 0.6981
0.250 0.3942 0.00792 0.00162 -0.0841 0.1368 0.7078
0.500 0.4214 0.00834 0.00178 -0.0841 0.0652 0.7160
0.750 0.4492 0.00854 0.00191 -0.0841 0.0442 0.7242
1.000 0.4771 0.00870 0.00207 -0.0841 0.0342 0.7316
1.250 0.5049 0.00888 0.00223 -0.0841 0.0252 0.7390
1.500 0.5326 0.00908 0.00240 -0.0841 0.0174 0.7454
1.750 0.5604 0.00929 0.00261 -0.0840 0.0133 0.7523
2.000 0.5879 0.00957 0.00292 -0.0838 0.0105 0.7582
2.250 0.6154 0.00984 0.00326 -0.0837 0.0098 0.7642
2.500 0.6429 0.01007 0.00353 -0.0836 0.0094 0.7699
2.750 0.6702 0.01037 0.00388 -0.0834 0.0090 0.7761
3.000 0.6973 0.01070 0.00428 -0.0832 0.0087 0.7824
3.250 0.7242 0.01106 0.00471 -0.0830 0.0083 0.7885
3.500 0.7510 0.01145 0.00518 -0.0827 0.0080 0.7946
3.750 0.7777 0.01185 0.00565 -0.0824 0.0076 0.8001
4.000 0.8043 0.01227 0.00613 -0.0822 0.0073 0.8059
4.250 0.8306 0.01276 0.00669 -0.0818 0.0069 0.8114
4.500 0.8558 0.01360 0.00765 -0.0813 0.0064 0.8173
5.000 0.9044 0.01616 0.01065 -0.0797 0.0059 0.8302
5.250 0.9301 0.01685 0.01146 -0.0793 0.0058 0.8364
5.500 0.9553 0.01759 0.01235 -0.0788 0.0056 0.8417
5.750 0.9796 0.01870 0.01365 -0.0781 0.0054 0.8472
6.000 1.0029 0.02020 0.01540 -0.0773 0.0053 0.8525
6.250 1.0249 0.02202 0.01752 -0.0762 0.0051 0.8587
6.500 1.0452 0.02436 0.02021 -0.0750 0.0050 0.8645
6.750 1.0616 0.02780 0.02411 -0.0732 0.0047 0.8703
7.000 1.0268 0.05128 0.04904 -0.0655 0.0041 0.8750
7.250 1.0253 0.05951 0.05758 -0.0642 0.0039 0.8810
7.500 1.0232 0.06674 0.06505 -0.0640 0.0038 0.8880
7.750 1.0169 0.07416 0.07266 -0.0648 0.0037 0.8954
8.250 0.9857 0.08953 0.08828 -0.0703 0.0037 0.9189
8.500 0.9590 0.09841 0.09724 -0.0780 0.0038 0.9539
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Polar data table (+)
Polar graphs
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