NASA SC(2)-0406 AIRFOIL (sc20406-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0406 AIRFOIL (sc20406-il) Reynolds number: 500,000 Max Cl/Cd: 52.94 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20406-il-500000.txt Download as CSV file: xf-sc20406-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6817 0.09078 0.08857 0.0094 1.0000 0.0179
-8.750 -0.6824 0.08578 0.08359 0.0058 1.0000 0.0182
-8.500 -0.6847 0.08022 0.07806 0.0009 1.0000 0.0184
-8.250 -0.6839 0.07208 0.06990 -0.0104 1.0000 0.0185
-8.000 -0.6794 0.06531 0.06302 -0.0170 1.0000 0.0189
-7.750 -0.6714 0.05907 0.05664 -0.0217 1.0000 0.0195
-6.500 -0.5850 0.02436 0.01951 -0.0315 1.0000 0.0155
-6.250 -0.5583 0.02257 0.01748 -0.0317 1.0000 0.0152
-6.000 -0.5319 0.01868 0.01310 -0.0323 1.0000 0.0155
-5.750 -0.5045 0.01651 0.01066 -0.0324 1.0000 0.0156
-5.500 -0.4769 0.01490 0.00887 -0.0324 1.0000 0.0154
-5.250 -0.4493 0.01298 0.00674 -0.0326 1.0000 0.0158
-5.000 -0.4210 0.01161 0.00526 -0.0329 1.0000 0.0170
-4.750 -0.3925 0.01094 0.00455 -0.0332 1.0000 0.0189
-4.500 -0.3639 0.01039 0.00394 -0.0335 1.0000 0.0214
-4.250 -0.3347 0.00969 0.00322 -0.0339 1.0000 0.0287
-4.000 -0.3061 0.00930 0.00281 -0.0341 1.0000 0.0444
-3.750 -0.2777 0.00894 0.00248 -0.0344 1.0000 0.0566
-3.500 -0.2494 0.00861 0.00221 -0.0347 1.0000 0.0745
-3.250 -0.2206 0.00811 0.00194 -0.0352 1.0000 0.1248
-3.000 -0.1903 0.00692 0.00159 -0.0368 1.0000 0.3426
-2.750 -0.1607 0.00608 0.00146 -0.0379 1.0000 0.5437
-2.500 -0.1329 0.00584 0.00143 -0.0379 1.0000 0.6142
-2.250 -0.1057 0.00570 0.00144 -0.0378 1.0000 0.6630
-2.000 -0.0787 0.00563 0.00144 -0.0375 1.0000 0.6959
-1.750 -0.0520 0.00558 0.00145 -0.0372 1.0000 0.7225
-1.500 -0.0256 0.00554 0.00150 -0.0368 1.0000 0.7474
-1.250 0.0006 0.00553 0.00155 -0.0364 1.0000 0.7685
-1.000 0.0266 0.00553 0.00163 -0.0359 1.0000 0.7909
-0.750 0.0519 0.00554 0.00173 -0.0352 1.0000 0.8120
-0.500 0.0776 0.00556 0.00182 -0.0347 1.0000 0.8281
-0.250 0.1037 0.00559 0.00191 -0.0343 1.0000 0.8403
0.000 0.1363 0.00557 0.00195 -0.0354 0.9968 0.8513
0.250 0.1832 0.00543 0.00187 -0.0395 0.9844 0.8599
0.500 0.2223 0.00534 0.00184 -0.0416 0.9621 0.8680
0.750 0.2530 0.00534 0.00185 -0.0417 0.9236 0.8776
1.000 0.2759 0.00541 0.00188 -0.0400 0.8773 0.8879
1.250 0.2970 0.00561 0.00188 -0.0379 0.8034 0.8984
1.500 0.3179 0.00612 0.00188 -0.0360 0.6655 0.9098
1.750 0.3385 0.00718 0.00203 -0.0347 0.4243 0.9223
2.000 0.3595 0.00815 0.00223 -0.0337 0.2171 0.9367
2.250 0.3802 0.00877 0.00242 -0.0324 0.1002 0.9567
2.500 0.4068 0.00906 0.00256 -0.0322 0.0643 1.0000
2.750 0.4372 0.00940 0.00286 -0.0329 0.0504 1.0000
3.000 0.4670 0.00977 0.00321 -0.0335 0.0373 1.0000
3.250 0.4962 0.01040 0.00381 -0.0338 0.0237 1.0000
3.500 0.5241 0.01139 0.00487 -0.0339 0.0198 1.0000
3.750 0.5527 0.01189 0.00542 -0.0341 0.0181 1.0000
4.000 0.5805 0.01268 0.00629 -0.0340 0.0168 1.0000
4.250 0.6081 0.01354 0.00723 -0.0340 0.0157 1.0000
4.500 0.6353 0.01464 0.00841 -0.0338 0.0148 1.0000
4.750 0.6620 0.01626 0.01022 -0.0335 0.0144 1.0000
5.000 0.6886 0.01864 0.01294 -0.0328 0.0148 1.0000
6.500 0.7845 0.05406 0.05122 -0.0283 0.0202 1.0000
6.750 0.7954 0.05933 0.05676 -0.0285 0.0201 1.0000
7.000 0.8081 0.06437 0.06204 -0.0294 0.0198 1.0000
7.250 0.8262 0.07014 0.06804 -0.0320 0.0179 1.0000
7.500 0.8306 0.07647 0.07449 -0.0355 0.0172 1.0000
7.750 0.8317 0.08283 0.08093 -0.0400 0.0168 1.0000
8.000 0.8278 0.08926 0.08740 -0.0459 0.0167 1.0000
8.250 0.8213 0.09542 0.09354 -0.0521 0.0166 1.0000
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Polar data table (+)
Polar graphs
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