PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Reynolds number: 50,000 Max Cl/Cd: 33.04 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pfcm-il-50000-n5.txt Download as CSV file: xf-pfcm-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5700 0.12866 0.12155 0.0014 1.0000 0.1063
-10.250 -0.5779 0.12594 0.11891 -0.0025 1.0000 0.1112
-10.000 -0.5897 0.12318 0.11627 -0.0076 1.0000 0.1122
-9.750 -0.5672 0.11723 0.11027 -0.0041 1.0000 0.1153
-9.500 -0.5618 0.11331 0.10638 -0.0049 1.0000 0.1180
-9.250 -0.5605 0.10950 0.10261 -0.0066 1.0000 0.1210
-9.000 -0.5765 0.10618 0.09946 -0.0124 1.0000 0.1267
-8.500 -0.5618 0.09010 0.08330 -0.0223 1.0000 0.0551
-8.250 -0.5606 0.08547 0.07872 -0.0246 1.0000 0.0529
-8.000 -0.5609 0.08025 0.07351 -0.0284 1.0000 0.0509
-7.750 -0.5617 0.07480 0.06801 -0.0322 1.0000 0.0487
-7.250 -0.5596 0.06381 0.05637 -0.0387 1.0000 0.0436
-7.000 -0.5509 0.05949 0.05189 -0.0391 1.0000 0.0431
-6.750 -0.5409 0.05527 0.04742 -0.0395 1.0000 0.0427
-6.500 -0.5292 0.05121 0.04299 -0.0396 1.0000 0.0427
-6.250 -0.5147 0.04767 0.03888 -0.0394 1.0000 0.0438
-6.000 -0.5007 0.04392 0.03497 -0.0392 1.0000 0.0459
-5.750 -0.4833 0.04090 0.03165 -0.0387 1.0000 0.0474
-5.500 -0.4639 0.03775 0.02802 -0.0379 1.0000 0.0474
-5.250 -0.4430 0.03494 0.02469 -0.0370 1.0000 0.0479
-5.000 -0.4210 0.03246 0.02180 -0.0360 1.0000 0.0487
-4.750 -0.3981 0.03027 0.01924 -0.0350 1.0000 0.0500
-4.500 -0.3748 0.02843 0.01708 -0.0339 1.0000 0.0528
-4.250 -0.3512 0.02698 0.01527 -0.0327 1.0000 0.0578
-4.000 -0.3290 0.02537 0.01366 -0.0316 1.0000 0.0622
-3.750 -0.3065 0.02409 0.01221 -0.0302 1.0000 0.0663
-3.500 -0.2842 0.02295 0.01081 -0.0289 1.0000 0.0718
-3.250 -0.2622 0.02190 0.00973 -0.0282 1.0000 0.0864
-3.000 -0.2399 0.02076 0.00860 -0.0275 1.0000 0.1067
-2.750 -0.2171 0.01835 0.00735 -0.0280 1.0000 0.2775
-2.500 -0.2114 0.01684 0.00768 -0.0220 1.0000 0.7101
-2.250 -0.1409 0.01664 0.00765 -0.0240 1.0000 0.9866
-2.000 -0.1192 0.01640 0.00712 -0.0244 1.0000 1.0000
-1.750 -0.1124 0.01625 0.00675 -0.0219 1.0000 1.0000
-1.500 -0.0980 0.01622 0.00647 -0.0206 1.0000 1.0000
-1.250 -0.0800 0.01626 0.00626 -0.0198 1.0000 1.0000
-1.000 -0.0602 0.01636 0.00611 -0.0193 1.0000 1.0000
-0.750 -0.0395 0.01651 0.00605 -0.0189 1.0000 1.0000
-0.500 -0.0183 0.01670 0.00607 -0.0186 1.0000 1.0000
-0.250 0.0031 0.01693 0.00615 -0.0184 1.0000 1.0000
0.000 0.0389 0.01722 0.00628 -0.0209 0.9932 1.0000
0.250 0.0785 0.01753 0.00648 -0.0242 0.9842 1.0000
0.500 0.1179 0.01784 0.00672 -0.0273 0.9752 1.0000
0.750 0.1564 0.01814 0.00699 -0.0302 0.9658 1.0000
1.000 0.1929 0.01844 0.00728 -0.0327 0.9554 1.0000
1.250 0.2293 0.01874 0.00760 -0.0350 0.9454 1.0000
1.500 0.2679 0.01905 0.00797 -0.0377 0.9362 1.0000
1.750 0.3049 0.01935 0.00839 -0.0401 0.9264 1.0000
2.000 0.3394 0.01965 0.00881 -0.0419 0.9156 1.0000
2.250 0.3742 0.01996 0.00926 -0.0437 0.9050 1.0000
2.500 0.4098 0.02025 0.00978 -0.0456 0.8950 1.0000
2.750 0.4444 0.02052 0.01027 -0.0471 0.8842 1.0000
3.000 0.4757 0.02081 0.01079 -0.0479 0.8715 1.0000
3.250 0.5074 0.02105 0.01130 -0.0486 0.8579 1.0000
3.500 0.5401 0.02119 0.01182 -0.0491 0.8428 1.0000
3.750 0.5728 0.02082 0.01178 -0.0481 0.8149 1.0000
4.000 0.5984 0.01908 0.01008 -0.0416 0.7259 1.0000
4.250 0.6156 0.01863 0.00928 -0.0360 0.5894 1.0000
4.500 0.6203 0.02059 0.00935 -0.0306 0.2484 1.0000
4.750 0.6317 0.02349 0.01115 -0.0292 0.1111 1.0000
5.000 0.6505 0.02521 0.01277 -0.0279 0.0893 1.0000
5.250 0.6707 0.02671 0.01434 -0.0267 0.0757 1.0000
5.500 0.6919 0.02824 0.01589 -0.0258 0.0651 1.0000
5.750 0.7177 0.02981 0.01774 -0.0247 0.0604 1.0000
6.000 0.7458 0.03170 0.01982 -0.0240 0.0566 1.0000
6.250 0.7733 0.03397 0.02225 -0.0235 0.0530 1.0000
6.500 0.7991 0.03633 0.02501 -0.0228 0.0485 1.0000
6.750 0.8235 0.03898 0.02812 -0.0220 0.0456 1.0000
7.000 0.8456 0.04209 0.03171 -0.0209 0.0443 1.0000
7.250 0.8643 0.04549 0.03560 -0.0197 0.0435 1.0000
7.500 0.8797 0.04913 0.03973 -0.0184 0.0429 1.0000
7.750 0.8927 0.05252 0.04345 -0.0172 0.0413 1.0000
8.250 0.9056 0.06049 0.05214 -0.0147 0.0383 1.0000
8.500 0.9064 0.06464 0.05674 -0.0133 0.0378 1.0000
8.750 0.9045 0.06898 0.06142 -0.0121 0.0378 1.0000
9.000 0.8993 0.07336 0.06607 -0.0112 0.0379 1.0000
9.250 0.8911 0.07775 0.07066 -0.0106 0.0381 1.0000
9.500 0.8794 0.08197 0.07504 -0.0101 0.0383 1.0000
9.750 0.8662 0.08639 0.07955 -0.0104 0.0385 1.0000
10.000 0.8537 0.09125 0.08448 -0.0117 0.0388 1.0000
10.250 0.8434 0.09650 0.08977 -0.0138 0.0391 1.0000
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Polar data table (+)
Polar graphs
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