PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.39 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pfcm-il-1000000.txt Download as CSV file: xf-pfcm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5944 0.08880 0.08725 -0.0088 1.0000 0.0079
-9.000 -0.5978 0.08327 0.08173 -0.0126 1.0000 0.0080
-8.750 -0.6011 0.07737 0.07586 -0.0175 1.0000 0.0080
-8.500 -0.6049 0.06902 0.06751 -0.0286 1.0000 0.0079
-8.250 -0.6062 0.06200 0.06040 -0.0343 1.0000 0.0080
-8.000 -0.6049 0.05590 0.05417 -0.0377 1.0000 0.0081
-7.750 -0.5988 0.05116 0.04929 -0.0395 1.0000 0.0082
-7.500 -0.5888 0.04749 0.04547 -0.0404 1.0000 0.0084
-7.250 -0.5769 0.04411 0.04195 -0.0408 1.0000 0.0087
-7.000 -0.5644 0.04104 0.03874 -0.0406 1.0000 0.0092
-6.750 -0.5525 0.03774 0.03526 -0.0395 1.0000 0.0102
-6.000 -0.4935 0.01875 0.01464 -0.0390 0.9953 0.0093
-5.750 -0.4616 0.01702 0.01269 -0.0402 0.9936 0.0101
-5.500 -0.4310 0.01472 0.01008 -0.0409 0.9910 0.0106
-5.250 -0.3986 0.01358 0.00876 -0.0420 0.9884 0.0113
-5.000 -0.3658 0.01300 0.00807 -0.0432 0.9855 0.0118
-4.750 -0.3343 0.01149 0.00640 -0.0442 0.9828 0.0122
-4.500 -0.3078 0.00998 0.00477 -0.0442 0.9762 0.0133
-4.250 -0.2782 0.00944 0.00419 -0.0447 0.9706 0.0144
-4.000 -0.2512 0.00899 0.00369 -0.0446 0.9629 0.0155
-3.750 -0.2245 0.00862 0.00325 -0.0443 0.9555 0.0165
-3.500 -0.1984 0.00829 0.00286 -0.0439 0.9468 0.0173
-3.250 -0.1722 0.00803 0.00255 -0.0435 0.9388 0.0180
-3.000 -0.1460 0.00762 0.00203 -0.0431 0.9300 0.0211
-2.750 -0.1191 0.00739 0.00176 -0.0428 0.9216 0.0265
-2.500 -0.0925 0.00710 0.00152 -0.0425 0.9132 0.0515
-2.250 -0.0659 0.00661 0.00133 -0.0426 0.9041 0.1438
-2.000 -0.0402 0.00579 0.00112 -0.0427 0.8953 0.3363
-1.750 -0.0146 0.00511 0.00101 -0.0426 0.8863 0.5240
-1.500 0.0125 0.00487 0.00098 -0.0426 0.8769 0.5975
-1.250 0.0398 0.00475 0.00096 -0.0425 0.8677 0.6448
-1.000 0.0674 0.00470 0.00093 -0.0424 0.8580 0.6707
-0.750 0.0948 0.00460 0.00094 -0.0423 0.8476 0.7149
-0.500 0.1221 0.00454 0.00094 -0.0421 0.8372 0.7495
-0.250 0.1498 0.00451 0.00093 -0.0420 0.8263 0.7700
0.000 0.1774 0.00449 0.00092 -0.0420 0.8148 0.7878
0.250 0.2051 0.00447 0.00091 -0.0419 0.8029 0.8035
0.500 0.2326 0.00444 0.00091 -0.0418 0.7903 0.8195
0.750 0.2597 0.00442 0.00092 -0.0416 0.7754 0.8401
1.000 0.2859 0.00439 0.00094 -0.0411 0.7577 0.8697
1.250 0.3098 0.00432 0.00097 -0.0401 0.7393 0.9181
1.500 0.3401 0.00433 0.00098 -0.0404 0.7143 0.9764
1.750 0.3740 0.00448 0.00098 -0.0419 0.6740 1.0000
2.000 0.4008 0.00467 0.00102 -0.0417 0.6349 1.0000
2.250 0.4276 0.00489 0.00110 -0.0416 0.5925 1.0000
2.500 0.4543 0.00514 0.00118 -0.0416 0.5450 1.0000
2.750 0.4802 0.00555 0.00131 -0.0414 0.4709 1.0000
3.000 0.5023 0.00668 0.00166 -0.0409 0.2771 1.0000
3.250 0.5255 0.00766 0.00203 -0.0406 0.1292 1.0000
3.500 0.5506 0.00830 0.00235 -0.0404 0.0536 1.0000
3.750 0.5765 0.00881 0.00273 -0.0402 0.0244 1.0000
4.000 0.6036 0.00906 0.00300 -0.0401 0.0218 1.0000
4.250 0.6303 0.00939 0.00333 -0.0400 0.0188 1.0000
4.500 0.6551 0.01010 0.00417 -0.0395 0.0160 1.0000
4.750 0.6815 0.01046 0.00456 -0.0393 0.0155 1.0000
5.000 0.7074 0.01090 0.00505 -0.0390 0.0149 1.0000
5.250 0.7328 0.01140 0.00560 -0.0387 0.0141 1.0000
5.500 0.7585 0.01184 0.00607 -0.0384 0.0130 1.0000
5.750 0.7841 0.01226 0.00652 -0.0382 0.0119 1.0000
6.000 0.8065 0.01333 0.00767 -0.0373 0.0110 1.0000
6.250 0.8258 0.01551 0.01003 -0.0359 0.0102 1.0000
6.500 0.8516 0.01591 0.01049 -0.0356 0.0099 1.0000
6.750 0.8764 0.01667 0.01134 -0.0351 0.0094 1.0000
7.000 0.9010 0.01742 0.01218 -0.0347 0.0087 1.0000
7.250 0.9258 0.01790 0.01274 -0.0344 0.0080 1.0000
7.500 0.9500 0.01848 0.01338 -0.0341 0.0075 1.0000
7.750 0.9731 0.01936 0.01434 -0.0336 0.0072 1.0000
8.000 0.9919 0.02163 0.01684 -0.0324 0.0068 1.0000
8.250 0.9975 0.02775 0.02365 -0.0293 0.0064 1.0000
8.500 1.0187 0.02867 0.02475 -0.0286 0.0062 1.0000
8.750 1.0321 0.03162 0.02805 -0.0268 0.0060 1.0000
9.000 1.0187 0.04124 0.03841 -0.0219 0.0057 1.0000
9.250 0.9959 0.05099 0.04868 -0.0177 0.0058 1.0000
9.500 0.9760 0.05764 0.05561 -0.0152 0.0061 1.0000
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Polar data table (+)
Polar graphs
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