NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il) Reynolds number: 1,000,000 Max Cl/Cd: 59.81 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20406-il-1000000.txt Download as CSV file: xf-sc20406-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0406 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.6124 0.01742 0.01305 -0.0320 1.0000 0.0090
-6.500 -0.5852 0.01581 0.01119 -0.0322 1.0000 0.0093
-6.250 -0.5576 0.01436 0.00953 -0.0325 1.0000 0.0094
-6.000 -0.5299 0.01314 0.00816 -0.0327 1.0000 0.0095
-5.750 -0.5019 0.01225 0.00716 -0.0329 1.0000 0.0097
-5.500 -0.4737 0.01114 0.00592 -0.0332 1.0000 0.0100
-5.250 -0.4448 0.00996 0.00457 -0.0337 1.0000 0.0103
-5.000 -0.4154 0.00910 0.00359 -0.0342 1.0000 0.0109
-4.750 -0.3863 0.00860 0.00304 -0.0346 1.0000 0.0124
-4.500 -0.3575 0.00827 0.00268 -0.0349 1.0000 0.0140
-4.250 -0.3286 0.00792 0.00229 -0.0351 1.0000 0.0173
-4.000 -0.2997 0.00759 0.00203 -0.0355 1.0000 0.0318
-3.750 -0.2713 0.00738 0.00186 -0.0357 1.0000 0.0420
-3.500 -0.2430 0.00718 0.00170 -0.0359 1.0000 0.0528
-3.250 -0.2147 0.00696 0.00156 -0.0361 1.0000 0.0713
-3.000 -0.1862 0.00667 0.00140 -0.0365 1.0000 0.1058
-2.750 -0.1573 0.00618 0.00124 -0.0371 1.0000 0.1970
-2.500 -0.1272 0.00531 0.00105 -0.0383 1.0000 0.3903
-2.250 -0.0984 0.00480 0.00098 -0.0390 1.0000 0.5226
-2.000 -0.0707 0.00461 0.00096 -0.0390 1.0000 0.5827
-1.750 -0.0435 0.00449 0.00096 -0.0390 1.0000 0.6216
-1.500 -0.0163 0.00440 0.00099 -0.0388 1.0000 0.6578
-1.250 0.0108 0.00435 0.00104 -0.0387 1.0000 0.6866
-1.000 0.0380 0.00432 0.00110 -0.0386 1.0000 0.7117
-0.750 0.0810 0.00419 0.00103 -0.0419 0.9929 0.7321
-0.500 0.1212 0.00412 0.00103 -0.0446 0.9734 0.7556
-0.250 0.1517 0.00413 0.00108 -0.0449 0.9492 0.7739
0.000 0.1764 0.00420 0.00112 -0.0438 0.9130 0.7864
0.250 0.2007 0.00436 0.00114 -0.0426 0.8623 0.7970
0.500 0.2263 0.00458 0.00115 -0.0419 0.7984 0.8075
0.750 0.2521 0.00496 0.00119 -0.0413 0.6941 0.8170
1.000 0.2783 0.00558 0.00129 -0.0412 0.5377 0.8258
1.500 0.3313 0.00716 0.00164 -0.0415 0.1822 0.8435
1.750 0.3586 0.00760 0.00181 -0.0415 0.1022 0.8526
2.000 0.3862 0.00789 0.00196 -0.0416 0.0649 0.8623
2.250 0.4136 0.00807 0.00214 -0.0414 0.0501 0.8717
2.500 0.4410 0.00824 0.00231 -0.0413 0.0400 0.8816
2.750 0.4683 0.00843 0.00249 -0.0411 0.0294 0.8921
3.000 0.4951 0.00874 0.00275 -0.0409 0.0161 0.9034
3.250 0.5213 0.00912 0.00324 -0.0403 0.0131 0.9154
3.500 0.5469 0.00939 0.00359 -0.0397 0.0125 0.9288
3.750 0.5707 0.00966 0.00396 -0.0387 0.0118 0.9462
4.000 0.5933 0.00992 0.00431 -0.0374 0.0110 1.0000
4.250 0.6217 0.01043 0.00486 -0.0375 0.0101 1.0000
4.500 0.6492 0.01126 0.00580 -0.0375 0.0094 1.0000
4.750 0.6759 0.01242 0.00708 -0.0372 0.0091 1.0000
5.000 0.7024 0.01371 0.00853 -0.0370 0.0091 1.0000
5.250 0.7280 0.01561 0.01065 -0.0365 0.0089 1.0000
5.500 0.7531 0.01782 0.01315 -0.0361 0.0088 1.0000
5.750 0.7781 0.01975 0.01534 -0.0356 0.0088 1.0000
6.000 0.8022 0.02192 0.01782 -0.0351 0.0089 1.0000
6.250 0.8244 0.02478 0.02104 -0.0343 0.0090 1.0000
6.500 0.8232 0.04250 0.04010 -0.0303 0.0101 1.0000
6.750 0.8385 0.04663 0.04445 -0.0302 0.0097 1.0000
7.000 0.8519 0.05062 0.04861 -0.0303 0.0094 1.0000
7.250 0.8622 0.05523 0.05340 -0.0307 0.0092 1.0000
7.500 0.8661 0.06154 0.05989 -0.0318 0.0089 1.0000
14.500 0.6585 0.17658 0.17524 -0.0703 0.0060 1.0000
14.750 0.6613 0.17925 0.17791 -0.0714 0.0059 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0406 AIRFOIL (sc20406-il)