NASA SC(2)-0010 AIRFOIL (sc20010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0010 AIRFOIL (sc20010-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.12 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20010-il-1000000-n5.txt Download as CSV file: xf-sc20010-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0010 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
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0395 0.14316 0.14108 0.0300 1.0000 0.0101
-17.500 -1.1403 0.11693 0.11459 0.0154 1.0000 0.0099
-17.250 -1.2108 0.09840 0.09585 0.0054 1.0000 0.0097
-17.000 -1.2677 0.08210 0.07932 -0.0040 1.0000 0.0096
-16.750 -1.3150 0.06778 0.06474 -0.0135 1.0000 0.0096
-16.500 -1.3408 0.05908 0.05584 -0.0191 1.0000 0.0096
-16.250 -1.3582 0.05293 0.04952 -0.0224 1.0000 0.0096
-16.000 -1.3692 0.04828 0.04472 -0.0242 1.0000 0.0096
-15.750 -1.3764 0.04449 0.04078 -0.0252 1.0000 0.0097
-15.500 -1.3860 0.04069 0.03683 -0.0256 1.0000 0.0097
-15.250 -1.3933 0.03745 0.03343 -0.0253 1.0000 0.0098
-15.000 -1.3975 0.03478 0.03063 -0.0245 1.0000 0.0099
-14.750 -1.3985 0.03261 0.02833 -0.0232 1.0000 0.0100
-14.500 -1.3970 0.03080 0.02640 -0.0215 1.0000 0.0100
-14.250 -1.3933 0.02930 0.02479 -0.0195 1.0000 0.0101
-14.000 -1.3879 0.02803 0.02343 -0.0172 1.0000 0.0102
-13.750 -1.3803 0.02694 0.02224 -0.0149 1.0000 0.0103
-13.500 -1.3677 0.02592 0.02113 -0.0134 1.0000 0.0104
-13.250 -1.3526 0.02500 0.02013 -0.0121 1.0000 0.0106
-13.000 -1.3360 0.02415 0.01919 -0.0110 1.0000 0.0107
-12.750 -1.3182 0.02334 0.01831 -0.0099 1.0000 0.0109
-12.500 -1.2997 0.02255 0.01744 -0.0090 1.0000 0.0110
-12.250 -1.2805 0.02177 0.01658 -0.0081 1.0000 0.0111
-12.000 -1.2607 0.02101 0.01574 -0.0072 1.0000 0.0113
-11.750 -1.2401 0.02030 0.01495 -0.0065 1.0000 0.0114
-11.500 -1.2189 0.01961 0.01419 -0.0057 1.0000 0.0115
-11.250 -1.1971 0.01896 0.01347 -0.0051 1.0000 0.0117
-11.000 -1.1748 0.01834 0.01278 -0.0045 1.0000 0.0118
-10.750 -1.1520 0.01775 0.01212 -0.0039 1.0000 0.0120
-10.500 -1.1288 0.01720 0.01150 -0.0034 1.0000 0.0121
-10.250 -1.1051 0.01668 0.01093 -0.0030 1.0000 0.0123
-10.000 -1.0811 0.01618 0.01037 -0.0026 1.0000 0.0124
-9.750 -1.0577 0.01556 0.00970 -0.0021 1.0000 0.0126
-9.500 -1.0337 0.01501 0.00911 -0.0016 1.0000 0.0130
-9.250 -1.0091 0.01453 0.00860 -0.0013 1.0000 0.0133
-9.000 -0.9842 0.01409 0.00813 -0.0010 1.0000 0.0136
-8.750 -0.9589 0.01369 0.00770 -0.0007 1.0000 0.0140
-8.500 -0.9333 0.01332 0.00730 -0.0004 1.0000 0.0144
-8.250 -0.9076 0.01296 0.00692 -0.0002 1.0000 0.0149
-8.000 -0.8818 0.01262 0.00655 0.0000 1.0000 0.0152
-7.750 -0.8558 0.01228 0.00619 0.0003 1.0000 0.0156
-7.500 -0.8301 0.01190 0.00580 0.0005 1.0000 0.0164
-7.250 -0.8040 0.01158 0.00547 0.0007 1.0000 0.0172
-7.000 -0.7732 0.01127 0.00516 -0.0001 0.9886 0.0183
-6.750 -0.7421 0.01098 0.00486 -0.0010 0.9752 0.0195
-6.500 -0.7127 0.01069 0.00457 -0.0014 0.9580 0.0215
-6.250 -0.6863 0.01049 0.00432 -0.0011 0.9367 0.0235
-6.000 -0.6614 0.01028 0.00409 -0.0005 0.9142 0.0263
-5.750 -0.6359 0.01012 0.00387 0.0001 0.8938 0.0289
-5.500 -0.6098 0.00995 0.00366 0.0004 0.8764 0.0322
-5.250 -0.5830 0.00980 0.00347 0.0006 0.8614 0.0351
-5.000 -0.5560 0.00963 0.00329 0.0008 0.8484 0.0385
-4.750 -0.5286 0.00951 0.00311 0.0009 0.8369 0.0407
-4.500 -0.5011 0.00935 0.00294 0.0009 0.8264 0.0440
-4.250 -0.4734 0.00920 0.00278 0.0010 0.8176 0.0471
-4.000 -0.4455 0.00908 0.00263 0.0009 0.8093 0.0496
-3.750 -0.4177 0.00892 0.00248 0.0009 0.8023 0.0551
-3.500 -0.3896 0.00878 0.00234 0.0009 0.7956 0.0609
-3.000 -0.3336 0.00847 0.00208 0.0008 0.7830 0.0783
-2.750 -0.3055 0.00831 0.00197 0.0007 0.7766 0.0927
-2.500 -0.2775 0.00815 0.00186 0.0006 0.7714 0.1108
-2.250 -0.2493 0.00796 0.00175 0.0005 0.7665 0.1326
-2.000 -0.2214 0.00775 0.00164 0.0004 0.7591 0.1664
-1.750 -0.1936 0.00752 0.00154 0.0004 0.7503 0.2074
-1.500 -0.1658 0.00729 0.00144 0.0003 0.7406 0.2527
-1.250 -0.1382 0.00696 0.00134 0.0002 0.7344 0.3206
-1.000 -0.1104 0.00661 0.00125 0.0000 0.7296 0.3948
-0.500 -0.0563 0.00581 0.00107 0.0000 0.7088 0.5868
-0.250 -0.0285 0.00563 0.00110 0.0000 0.6992 0.6589
0.000 0.0000 0.00560 0.00111 0.0000 0.6879 0.6876
0.250 0.0285 0.00563 0.00110 0.0000 0.6588 0.6993
0.500 0.0563 0.00579 0.00107 0.0000 0.5905 0.7084
1.000 0.1104 0.00661 0.00125 0.0000 0.3954 0.7296
1.250 0.1381 0.00696 0.00134 -0.0002 0.3198 0.7345
1.500 0.1657 0.00729 0.00144 -0.0003 0.2519 0.7406
1.750 0.1935 0.00752 0.00154 -0.0003 0.2073 0.7505
2.000 0.2213 0.00775 0.00164 -0.0004 0.1664 0.7593
2.250 0.2492 0.00796 0.00175 -0.0005 0.1326 0.7664
2.500 0.2774 0.00815 0.00186 -0.0006 0.1108 0.7714
2.750 0.3055 0.00831 0.00197 -0.0007 0.0927 0.7766
3.000 0.3335 0.00847 0.00208 -0.0008 0.0784 0.7829
3.500 0.3896 0.00878 0.00234 -0.0009 0.0609 0.7955
3.750 0.4177 0.00892 0.00248 -0.0009 0.0551 0.8023
4.000 0.4455 0.00908 0.00263 -0.0009 0.0496 0.8092
4.250 0.4734 0.00920 0.00278 -0.0010 0.0471 0.8176
4.500 0.5011 0.00934 0.00294 -0.0009 0.0440 0.8264
4.750 0.5286 0.00951 0.00311 -0.0009 0.0407 0.8369
5.000 0.5560 0.00963 0.00329 -0.0008 0.0385 0.8484
5.250 0.5830 0.00980 0.00347 -0.0006 0.0350 0.8614
5.500 0.6097 0.00995 0.00366 -0.0004 0.0321 0.8764
5.750 0.6359 0.01012 0.00387 -0.0001 0.0289 0.8938
6.000 0.6614 0.01028 0.00409 0.0005 0.0263 0.9142
6.250 0.6863 0.01048 0.00432 0.0011 0.0236 0.9368
6.500 0.7127 0.01069 0.00457 0.0014 0.0216 0.9581
6.750 0.7422 0.01098 0.00485 0.0010 0.0195 0.9753
7.000 0.7732 0.01127 0.00516 0.0001 0.0183 0.9887
7.250 0.8040 0.01157 0.00547 -0.0007 0.0172 1.0000
7.500 0.8301 0.01190 0.00580 -0.0005 0.0164 1.0000
7.750 0.8558 0.01228 0.00619 -0.0003 0.0156 1.0000
8.000 0.8818 0.01262 0.00655 0.0000 0.0152 1.0000
8.250 0.9076 0.01296 0.00692 0.0002 0.0149 1.0000
8.500 0.9333 0.01331 0.00730 0.0004 0.0144 1.0000
8.750 0.9589 0.01369 0.00770 0.0007 0.0140 1.0000
9.000 0.9841 0.01409 0.00813 0.0010 0.0136 1.0000
9.250 1.0091 0.01453 0.00860 0.0013 0.0133 1.0000
9.500 1.0337 0.01501 0.00911 0.0016 0.0130 1.0000
9.750 1.0577 0.01556 0.00970 0.0021 0.0126 1.0000
10.000 1.0811 0.01618 0.01037 0.0026 0.0124 1.0000
10.250 1.1051 0.01667 0.01092 0.0030 0.0123 1.0000
10.500 1.1288 0.01720 0.01150 0.0034 0.0121 1.0000
10.750 1.1521 0.01775 0.01212 0.0039 0.0120 1.0000
11.000 1.1748 0.01834 0.01277 0.0045 0.0118 1.0000
11.250 1.1972 0.01896 0.01347 0.0051 0.0117 1.0000
11.500 1.2189 0.01961 0.01419 0.0057 0.0115 1.0000
11.750 1.2401 0.02030 0.01495 0.0064 0.0114 1.0000
12.000 1.2607 0.02102 0.01574 0.0072 0.0113 1.0000
12.250 1.2806 0.02177 0.01657 0.0080 0.0111 1.0000
12.500 1.2998 0.02254 0.01744 0.0089 0.0110 1.0000
12.750 1.3185 0.02333 0.01830 0.0099 0.0108 1.0000
13.000 1.3363 0.02414 0.01919 0.0109 0.0107 1.0000
13.250 1.3530 0.02499 0.02011 0.0120 0.0106 1.0000
13.500 1.3681 0.02592 0.02112 0.0133 0.0104 1.0000
13.750 1.3808 0.02693 0.02223 0.0149 0.0103 1.0000
14.000 1.3886 0.02803 0.02342 0.0171 0.0102 1.0000
14.250 1.3940 0.02930 0.02479 0.0194 0.0101 1.0000
14.500 1.3979 0.03080 0.02640 0.0214 0.0100 1.0000
14.750 1.3993 0.03261 0.02832 0.0230 0.0099 1.0000
15.000 1.3980 0.03481 0.03066 0.0244 0.0099 1.0000
15.250 1.3941 0.03747 0.03345 0.0252 0.0098 1.0000
15.500 1.3864 0.04076 0.03690 0.0254 0.0097 1.0000
15.750 1.3780 0.04443 0.04073 0.0250 0.0097 1.0000
16.000 1.3712 0.04819 0.04462 0.0240 0.0096 1.0000
16.250 1.3598 0.05290 0.04949 0.0222 0.0096 1.0000
16.500 1.3430 0.05897 0.05573 0.0189 0.0096 1.0000
16.750 1.3177 0.06756 0.06452 0.0134 0.0096 1.0000
17.000 1.2710 0.08180 0.07902 0.0038 0.0096 1.0000
17.250 1.2120 0.09854 0.09599 -0.0058 0.0097 1.0000
17.500 1.1416 0.11706 0.11473 -0.0158 0.0099 1.0000
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Polar data table (+)
Polar graphs
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