NASA SC(2)-0404 AIRFOIL (sc20404-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0404 AIRFOIL (sc20404-il) Reynolds number: 200,000 Max Cl/Cd: 35.18 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20404-il-200000.txt Download as CSV file: xf-sc20404-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0404 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6592 0.09901 0.09552 0.0167 1.0000 0.0258
-8.250 -0.6566 0.09487 0.09142 0.0140 1.0000 0.0265
-8.000 -0.6541 0.09065 0.08723 0.0108 1.0000 0.0272
-7.750 -0.6494 0.08595 0.08256 0.0057 1.0000 0.0279
-7.500 -0.6378 0.07999 0.07659 -0.0036 1.0000 0.0287
-7.250 -0.6202 0.07411 0.07058 -0.0130 1.0000 0.0296
-7.000 -0.6025 0.06940 0.06566 -0.0186 1.0000 0.0300
-6.750 -0.5858 0.06494 0.06097 -0.0220 1.0000 0.0302
-6.500 -0.5761 0.05696 0.05283 -0.0258 1.0000 0.0310
-6.250 -0.5643 0.05195 0.04788 -0.0268 1.0000 0.0325
-6.000 -0.5460 0.04814 0.04395 -0.0284 1.0000 0.0346
-5.750 -0.5229 0.04405 0.03962 -0.0304 1.0000 0.0377
-5.500 -0.4870 0.04317 0.03790 -0.0318 1.0000 0.0430
-5.250 -0.4695 0.03532 0.03011 -0.0343 1.0000 0.0462
-5.000 -0.4392 0.03265 0.02673 -0.0356 1.0000 0.0571
-4.750 -0.4149 0.02918 0.02322 -0.0368 1.0000 0.0716
-4.500 -0.3889 0.02687 0.02081 -0.0376 1.0000 0.0907
-4.250 -0.3473 0.02100 0.01388 -0.0362 1.0000 0.0384
-4.000 -0.3155 0.01881 0.01109 -0.0353 1.0000 0.0308
-3.750 -0.2871 0.01664 0.00870 -0.0350 1.0000 0.0299
-3.500 -0.2590 0.01475 0.00666 -0.0347 1.0000 0.0306
-3.250 -0.2312 0.01292 0.00486 -0.0349 1.0000 0.0372
-3.000 -0.2023 0.01186 0.00374 -0.0351 1.0000 0.0453
-2.750 -0.1685 0.00927 0.00226 -0.0376 1.0000 0.3085
-2.500 -0.1479 0.00787 0.00244 -0.0358 1.0000 0.7507
-2.250 -0.1299 0.00781 0.00250 -0.0326 1.0000 0.8198
-2.000 -0.1101 0.00773 0.00241 -0.0302 1.0000 0.8527
-1.750 -0.0948 0.00760 0.00231 -0.0267 1.0000 0.8887
-1.500 -0.0884 0.00730 0.00209 -0.0209 1.0000 0.9323
-1.250 -0.0668 0.00696 0.00176 -0.0190 1.0000 0.9881
-1.000 -0.0366 0.00689 0.00162 -0.0201 1.0000 1.0000
-0.750 -0.0050 0.00688 0.00153 -0.0215 1.0000 1.0000
-0.500 0.0261 0.00688 0.00149 -0.0227 1.0000 1.0000
-0.250 0.0567 0.00690 0.00149 -0.0237 1.0000 1.0000
0.000 0.0867 0.00694 0.00152 -0.0245 1.0000 1.0000
0.250 0.1162 0.00698 0.00159 -0.0252 1.0000 1.0000
0.500 0.1452 0.00703 0.00172 -0.0257 1.0000 1.0000
0.750 0.1739 0.00709 0.00186 -0.0261 1.0000 1.0000
1.000 0.2022 0.00717 0.00203 -0.0264 1.0000 1.0000
1.250 0.2305 0.00725 0.00225 -0.0267 1.0000 1.0000
1.500 0.2586 0.00735 0.00253 -0.0269 1.0000 1.0000
1.750 0.3176 0.01109 0.00288 -0.0326 0.0641 1.0000
2.000 0.3451 0.01236 0.00423 -0.0323 0.0419 1.0000
2.250 0.3724 0.01368 0.00560 -0.0319 0.0391 1.0000
2.500 0.4001 0.01463 0.00654 -0.0319 0.0302 1.0000
2.750 0.4276 0.01742 0.00949 -0.0314 0.0286 1.0000
3.000 0.4566 0.01906 0.01135 -0.0309 0.0292 1.0000
3.250 0.4880 0.02164 0.01454 -0.0296 0.0365 1.0000
3.500 0.5264 0.02728 0.02124 -0.0268 0.0869 1.0000
3.750 0.5521 0.02982 0.02406 -0.0266 0.0737 1.0000
4.000 0.5767 0.03284 0.02736 -0.0265 0.0623 1.0000
4.250 0.6000 0.03532 0.03011 -0.0265 0.0462 1.0000
4.500 0.6197 0.03934 0.03414 -0.0269 0.0422 1.0000
4.750 0.6457 0.04343 0.03896 -0.0265 0.0374 1.0000
5.000 0.6688 0.04738 0.04321 -0.0269 0.0337 1.0000
5.250 0.6879 0.05123 0.04724 -0.0273 0.0314 1.0000
5.500 0.7023 0.05534 0.05139 -0.0277 0.0297 1.0000
5.750 0.7068 0.06424 0.06034 -0.0292 0.0284 1.0000
6.000 0.7233 0.06865 0.06501 -0.0304 0.0283 1.0000
6.250 0.7406 0.07292 0.06951 -0.0323 0.0280 1.0000
6.500 0.7620 0.07750 0.07435 -0.0369 0.0270 1.0000
6.750 0.7767 0.08293 0.07990 -0.0422 0.0258 1.0000
7.000 0.7859 0.08832 0.08534 -0.0472 0.0250 1.0000
7.250 0.7920 0.09360 0.09065 -0.0522 0.0243 1.0000
7.500 0.7936 0.09853 0.09557 -0.0569 0.0239 1.0000
7.750 0.7938 0.10313 0.10013 -0.0604 0.0235 1.0000
8.000 0.7945 0.10759 0.10457 -0.0633 0.0230 1.0000
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Polar data table (+)
Polar graphs
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