PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Reynolds number: 500,000 Max Cl/Cd: 67.3 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pfcm-il-500000-n5.txt Download as CSV file: xf-pfcm-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5994 0.08288 0.08071 -0.0132 1.0000 0.0051
-8.750 -0.6065 0.07607 0.07397 -0.0190 1.0000 0.0050
-8.500 -0.6177 0.06596 0.06382 -0.0310 1.0000 0.0049
-8.250 -0.6207 0.05846 0.05618 -0.0363 1.0000 0.0049
-8.000 -0.6185 0.05216 0.04970 -0.0391 1.0000 0.0050
-7.750 -0.6124 0.04654 0.04386 -0.0405 1.0000 0.0051
-7.500 -0.6037 0.04127 0.03833 -0.0408 1.0000 0.0053
-7.250 -0.5948 0.03549 0.03219 -0.0403 1.0000 0.0056
-7.000 -0.5877 0.02840 0.02453 -0.0385 1.0000 0.0060
-6.750 -0.5746 0.02300 0.01851 -0.0367 0.9997 0.0069
-6.500 -0.5450 0.02058 0.01564 -0.0378 0.9965 0.0075
-6.250 -0.5171 0.01734 0.01191 -0.0387 0.9933 0.0082
-6.000 -0.4862 0.01643 0.01088 -0.0398 0.9896 0.0088
-5.750 -0.4547 0.01553 0.00984 -0.0410 0.9863 0.0095
-5.500 -0.4248 0.01461 0.00877 -0.0417 0.9813 0.0103
-5.250 -0.3932 0.01402 0.00808 -0.0428 0.9771 0.0114
-5.000 -0.3632 0.01342 0.00734 -0.0434 0.9714 0.0121
-4.750 -0.3331 0.01257 0.00639 -0.0441 0.9659 0.0126
-4.500 -0.3059 0.01141 0.00509 -0.0442 0.9587 0.0134
-4.000 -0.2498 0.01040 0.00397 -0.0446 0.9435 0.0156
-3.750 -0.2224 0.00997 0.00344 -0.0445 0.9356 0.0163
-3.500 -0.1953 0.00963 0.00302 -0.0443 0.9269 0.0175
-3.250 -0.1683 0.00935 0.00267 -0.0442 0.9182 0.0191
-3.000 -0.1414 0.00910 0.00234 -0.0440 0.9096 0.0218
-2.750 -0.1144 0.00886 0.00209 -0.0438 0.9004 0.0299
-2.500 -0.0873 0.00865 0.00188 -0.0437 0.8914 0.0448
-2.250 -0.0606 0.00830 0.00169 -0.0436 0.8825 0.0950
-2.000 -0.0348 0.00752 0.00147 -0.0437 0.8728 0.2613
-1.750 -0.0100 0.00659 0.00132 -0.0438 0.8634 0.4967
-1.500 0.0168 0.00638 0.00125 -0.0436 0.8539 0.5617
-1.250 0.0435 0.00619 0.00124 -0.0434 0.8438 0.6265
-1.000 0.0696 0.00600 0.00127 -0.0429 0.8335 0.7005
-0.500 0.1242 0.00592 0.00122 -0.0426 0.8120 0.7447
-0.250 0.1518 0.00591 0.00119 -0.0425 0.8007 0.7573
0.000 0.1795 0.00590 0.00118 -0.0424 0.7893 0.7692
0.250 0.2071 0.00590 0.00117 -0.0423 0.7781 0.7815
0.500 0.2346 0.00589 0.00117 -0.0422 0.7674 0.7948
0.750 0.2619 0.00589 0.00119 -0.0421 0.7567 0.8091
1.000 0.2890 0.00588 0.00122 -0.0419 0.7457 0.8262
1.250 0.3154 0.00586 0.00127 -0.0415 0.7338 0.8487
1.500 0.3406 0.00584 0.00131 -0.0407 0.7172 0.8815
1.750 0.3666 0.00584 0.00135 -0.0401 0.6943 0.9295
2.000 0.4004 0.00601 0.00136 -0.0414 0.6453 0.9798
2.250 0.4287 0.00637 0.00143 -0.0416 0.5695 1.0000
2.500 0.4531 0.00688 0.00155 -0.0412 0.4778 1.0000
2.750 0.4745 0.00798 0.00188 -0.0406 0.2951 1.0000
3.000 0.4978 0.00888 0.00223 -0.0403 0.1644 1.0000
3.250 0.5227 0.00949 0.00256 -0.0401 0.0910 1.0000
3.500 0.5485 0.00994 0.00284 -0.0400 0.0533 1.0000
3.750 0.5747 0.01029 0.00312 -0.0399 0.0343 1.0000
4.000 0.6011 0.01063 0.00344 -0.0397 0.0254 1.0000
4.250 0.6273 0.01097 0.00378 -0.0396 0.0210 1.0000
4.500 0.6531 0.01143 0.00430 -0.0393 0.0183 1.0000
4.750 0.6787 0.01190 0.00484 -0.0390 0.0172 1.0000
5.000 0.7043 0.01233 0.00533 -0.0387 0.0165 1.0000
5.250 0.7296 0.01281 0.00588 -0.0383 0.0156 1.0000
5.500 0.7549 0.01327 0.00639 -0.0380 0.0142 1.0000
5.750 0.7796 0.01380 0.00700 -0.0376 0.0132 1.0000
6.000 0.8040 0.01441 0.00767 -0.0372 0.0123 1.0000
6.250 0.8266 0.01534 0.00867 -0.0365 0.0112 1.0000
6.500 0.8493 0.01630 0.00973 -0.0358 0.0102 1.0000
6.750 0.8738 0.01689 0.01041 -0.0353 0.0096 1.0000
7.000 0.8973 0.01773 0.01136 -0.0347 0.0089 1.0000
7.250 0.9206 0.01860 0.01235 -0.0342 0.0081 1.0000
7.500 0.9440 0.01939 0.01327 -0.0336 0.0075 1.0000
7.750 0.9673 0.02008 0.01403 -0.0332 0.0071 1.0000
8.000 0.9870 0.02172 0.01582 -0.0322 0.0064 1.0000
8.250 1.0100 0.02252 0.01679 -0.0317 0.0060 1.0000
8.500 1.0307 0.02396 0.01847 -0.0308 0.0055 1.0000
8.750 1.0489 0.02601 0.02084 -0.0295 0.0051 1.0000
9.000 1.0652 0.02827 0.02342 -0.0282 0.0048 1.0000
9.250 1.0801 0.03054 0.02599 -0.0268 0.0045 1.0000
9.500 1.0943 0.03260 0.02831 -0.0254 0.0043 1.0000
9.750 1.1070 0.03463 0.03062 -0.0240 0.0041 1.0000
10.000 1.1168 0.03692 0.03316 -0.0224 0.0040 1.0000
10.250 1.1124 0.04144 0.03811 -0.0197 0.0039 1.0000
10.500 1.0630 0.05257 0.04987 -0.0140 0.0038 1.0000
10.750 1.0170 0.06122 0.05884 -0.0113 0.0038 1.0000
11.000 0.9711 0.07131 0.06917 -0.0139 0.0039 1.0000
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Polar data table (+)
Polar graphs
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