PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Reynolds number: 100,000 Max Cl/Cd: 46.95 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pfcm-il-100000.txt Download as CSV file: xf-pfcm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: PROPFAN CRUISE MISSILE WING AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5628 0.09756 0.09275 -0.0114 1.0000 0.0892
-8.500 -0.5758 0.09306 0.08836 -0.0196 1.0000 0.0913
-8.250 -0.5911 0.08792 0.08314 -0.0306 1.0000 0.0920
-8.000 -0.5659 0.08463 0.07999 -0.0195 1.0000 0.0971
-7.750 -0.5646 0.07998 0.07535 -0.0242 1.0000 0.1017
-7.500 -0.5840 0.07551 0.07044 -0.0369 1.0000 0.1058
-7.250 -0.5181 0.05869 0.05419 -0.0368 1.0000 0.1202
-7.000 -0.5658 0.06621 0.06112 -0.0377 1.0000 0.1202
-6.750 -0.5479 0.06252 0.05771 -0.0343 1.0000 0.1273
-6.500 -0.5401 0.05890 0.05398 -0.0350 1.0000 0.1404
-6.000 -0.5233 0.05227 0.04716 -0.0356 1.0000 0.1776
-5.750 -0.5108 0.04945 0.04437 -0.0341 1.0000 0.1955
-5.500 -0.5006 0.04679 0.04170 -0.0327 1.0000 0.2220
-5.250 -0.4895 0.04450 0.03946 -0.0306 1.0000 0.2526
-5.000 -0.4449 0.03678 0.02957 -0.0366 1.0000 0.1332
-4.750 -0.4128 0.02952 0.02147 -0.0348 1.0000 0.0729
-4.500 -0.3876 0.02731 0.01842 -0.0329 1.0000 0.0658
-4.250 -0.3662 0.02472 0.01576 -0.0322 1.0000 0.0691
-4.000 -0.3421 0.02285 0.01354 -0.0310 1.0000 0.0687
-3.750 -0.3176 0.02116 0.01162 -0.0298 1.0000 0.0689
-3.500 -0.2935 0.01973 0.01011 -0.0288 1.0000 0.0711
-3.250 -0.2697 0.01857 0.00889 -0.0278 1.0000 0.0756
-3.000 -0.2467 0.01740 0.00783 -0.0271 1.0000 0.0862
-2.750 -0.2232 0.01632 0.00680 -0.0263 1.0000 0.0992
-2.500 -0.1965 0.01334 0.00549 -0.0272 1.0000 0.3930
-2.250 -0.1926 0.01233 0.00595 -0.0195 1.0000 0.8072
-2.000 -0.1799 0.01220 0.00597 -0.0143 1.0000 0.9039
-1.750 -0.1175 0.01223 0.00575 -0.0205 1.0000 1.0000
-1.500 -0.1063 0.01217 0.00549 -0.0191 1.0000 1.0000
-1.250 -0.0860 0.01224 0.00533 -0.0190 1.0000 1.0000
-1.000 -0.0637 0.01239 0.00530 -0.0191 1.0000 1.0000
-0.750 -0.0410 0.01259 0.00534 -0.0193 1.0000 1.0000
-0.500 -0.0182 0.01284 0.00546 -0.0194 1.0000 1.0000
-0.250 0.0045 0.01312 0.00563 -0.0195 1.0000 1.0000
0.000 0.0271 0.01345 0.00585 -0.0197 1.0000 1.0000
0.250 0.0506 0.01382 0.00615 -0.0201 0.9996 1.0000
0.500 0.0965 0.01422 0.00648 -0.0247 0.9915 1.0000
0.750 0.1427 0.01462 0.00686 -0.0293 0.9836 1.0000
1.000 0.1848 0.01497 0.00720 -0.0330 0.9740 1.0000
1.250 0.2282 0.01532 0.00758 -0.0369 0.9652 1.0000
1.500 0.2727 0.01564 0.00795 -0.0409 0.9565 1.0000
1.750 0.3111 0.01594 0.00834 -0.0436 0.9456 1.0000
2.000 0.3513 0.01622 0.00873 -0.0466 0.9355 1.0000
2.250 0.3998 0.01638 0.00905 -0.0510 0.9275 1.0000
2.500 0.4388 0.01655 0.00941 -0.0534 0.9154 1.0000
2.750 0.4784 0.01660 0.00965 -0.0556 0.9024 1.0000
3.000 0.5248 0.01610 0.00940 -0.0576 0.8855 1.0000
3.250 0.5586 0.01455 0.00803 -0.0539 0.8442 1.0000
3.500 0.5782 0.01365 0.00719 -0.0488 0.7975 1.0000
3.750 0.5979 0.01311 0.00666 -0.0446 0.7420 1.0000
4.000 0.6113 0.01302 0.00608 -0.0387 0.5849 1.0000
4.250 0.6064 0.01726 0.00732 -0.0331 0.1142 1.0000
4.500 0.6259 0.01879 0.00873 -0.0315 0.0889 1.0000
4.750 0.6469 0.02032 0.01022 -0.0300 0.0794 1.0000
5.000 0.6700 0.02207 0.01188 -0.0291 0.0710 1.0000
5.250 0.6964 0.02361 0.01352 -0.0284 0.0656 1.0000
5.500 0.7239 0.02562 0.01562 -0.0278 0.0630 1.0000
5.750 0.7518 0.02804 0.01822 -0.0271 0.0622 1.0000
6.000 0.7778 0.03111 0.02150 -0.0266 0.0607 1.0000
6.250 0.8009 0.03403 0.02492 -0.0254 0.0589 1.0000
6.500 0.8258 0.03703 0.02829 -0.0243 0.0609 1.0000
6.750 0.8465 0.04182 0.03395 -0.0219 0.0711 1.0000
10.500 0.6768 0.11450 0.11012 -0.0216 0.1255 1.0000
10.750 0.6468 0.11959 0.11509 -0.0270 0.1223 1.0000
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Polar data table (+)
Polar graphs
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