PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.92 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pfcm-il-1000000-n5.txt Download as CSV file: xf-pfcm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6031 0.12609 0.12445 0.0104 1.0000 0.0033
-10.750 -0.6011 0.11670 0.11508 0.0065 1.0000 0.0032
-8.750 -0.7693 0.02111 0.01752 -0.0391 1.0000 0.0036
-8.500 -0.7496 0.01905 0.01515 -0.0384 1.0000 0.0038
-8.250 -0.7286 0.01749 0.01332 -0.0378 1.0000 0.0040
-8.000 -0.7069 0.01627 0.01191 -0.0371 1.0000 0.0042
-7.750 -0.6792 0.01519 0.01064 -0.0377 0.9977 0.0044
-7.500 -0.6495 0.01411 0.00938 -0.0386 0.9946 0.0046
-7.250 -0.6200 0.01343 0.00862 -0.0395 0.9903 0.0050
-7.000 -0.5887 0.01315 0.00831 -0.0406 0.9864 0.0053
-6.750 -0.5589 0.01286 0.00799 -0.0413 0.9809 0.0058
-6.500 -0.5285 0.01258 0.00765 -0.0421 0.9756 0.0064
-6.250 -0.5001 0.01218 0.00717 -0.0425 0.9684 0.0070
-6.000 -0.4723 0.01177 0.00669 -0.0427 0.9611 0.0073
-5.750 -0.4454 0.01141 0.00625 -0.0426 0.9527 0.0075
-5.500 -0.4208 0.01040 0.00510 -0.0422 0.9434 0.0084
-5.250 -0.3947 0.01003 0.00467 -0.0419 0.9347 0.0090
-5.000 -0.3683 0.00983 0.00442 -0.0417 0.9257 0.0097
-4.750 -0.3417 0.00957 0.00411 -0.0416 0.9167 0.0104
-4.500 -0.3152 0.00924 0.00370 -0.0414 0.9082 0.0108
-4.250 -0.2885 0.00891 0.00329 -0.0412 0.8992 0.0112
-4.000 -0.2614 0.00861 0.00292 -0.0411 0.8905 0.0115
-3.750 -0.2342 0.00840 0.00263 -0.0410 0.8820 0.0119
-3.500 -0.2068 0.00817 0.00233 -0.0410 0.8730 0.0122
-3.250 -0.1792 0.00795 0.00204 -0.0410 0.8645 0.0126
-3.000 -0.1516 0.00771 0.00171 -0.0409 0.8555 0.0151
-2.750 -0.1238 0.00755 0.00154 -0.0410 0.8459 0.0185
-2.500 -0.0959 0.00742 0.00138 -0.0410 0.8364 0.0254
-2.250 -0.0681 0.00729 0.00126 -0.0411 0.8259 0.0367
-2.000 -0.0402 0.00715 0.00114 -0.0412 0.8150 0.0564
-1.750 -0.0124 0.00695 0.00103 -0.0413 0.8034 0.0941
-1.500 0.0147 0.00639 0.00088 -0.0416 0.7918 0.2347
-1.250 0.0409 0.00557 0.00074 -0.0419 0.7804 0.4585
-1.000 0.0687 0.00541 0.00070 -0.0420 0.7696 0.5148
-0.500 0.1237 0.00504 0.00072 -0.0421 0.7483 0.6586
-0.250 0.1518 0.00501 0.00072 -0.0422 0.7387 0.6855
0.000 0.1798 0.00499 0.00073 -0.0423 0.7288 0.7049
0.250 0.2081 0.00500 0.00075 -0.0424 0.7185 0.7181
0.750 0.2644 0.00506 0.00078 -0.0426 0.6923 0.7392
1.000 0.2922 0.00513 0.00081 -0.0426 0.6707 0.7497
1.250 0.3198 0.00522 0.00085 -0.0427 0.6454 0.7608
1.500 0.3469 0.00539 0.00089 -0.0426 0.6015 0.7720
1.750 0.3724 0.00581 0.00098 -0.0423 0.5086 0.7838
2.000 0.3958 0.00666 0.00120 -0.0420 0.3395 0.7971
2.500 0.4463 0.00758 0.00162 -0.0415 0.1676 0.8324
2.750 0.4707 0.00792 0.00183 -0.0410 0.1017 0.8662
3.000 0.4929 0.00807 0.00202 -0.0398 0.0647 0.9301
3.250 0.5260 0.00830 0.00221 -0.0411 0.0393 0.9970
3.500 0.5533 0.00855 0.00240 -0.0412 0.0260 1.0000
3.750 0.5803 0.00880 0.00260 -0.0411 0.0184 1.0000
4.000 0.6075 0.00901 0.00283 -0.0411 0.0166 1.0000
4.250 0.6345 0.00924 0.00307 -0.0411 0.0156 1.0000
4.500 0.6614 0.00949 0.00336 -0.0410 0.0146 1.0000
4.750 0.6881 0.00977 0.00365 -0.0410 0.0137 1.0000
5.000 0.7146 0.01008 0.00397 -0.0408 0.0125 1.0000
5.250 0.7402 0.01057 0.00453 -0.0405 0.0110 1.0000
5.500 0.7658 0.01102 0.00504 -0.0402 0.0104 1.0000
5.750 0.7923 0.01127 0.00533 -0.0402 0.0100 1.0000
6.000 0.8185 0.01156 0.00564 -0.0401 0.0094 1.0000
6.250 0.8443 0.01192 0.00604 -0.0399 0.0088 1.0000
6.500 0.8700 0.01228 0.00643 -0.0397 0.0081 1.0000
6.750 0.8957 0.01263 0.00680 -0.0395 0.0075 1.0000
7.000 0.9206 0.01309 0.00728 -0.0392 0.0068 1.0000
7.250 0.9446 0.01373 0.00801 -0.0387 0.0063 1.0000
7.500 0.9700 0.01406 0.00839 -0.0385 0.0059 1.0000
7.750 0.9951 0.01445 0.00882 -0.0383 0.0054 1.0000
8.000 1.0197 0.01490 0.00932 -0.0379 0.0049 1.0000
8.250 1.0444 0.01532 0.00977 -0.0376 0.0045 1.0000
8.500 1.0684 0.01583 0.01031 -0.0373 0.0042 1.0000
8.750 1.0896 0.01687 0.01146 -0.0364 0.0037 1.0000
9.000 1.1123 0.01757 0.01228 -0.0358 0.0036 1.0000
9.250 1.1345 0.01836 0.01320 -0.0352 0.0035 1.0000
9.500 1.1561 0.01922 0.01419 -0.0344 0.0033 1.0000
9.750 1.1771 0.02015 0.01525 -0.0337 0.0031 1.0000
10.000 1.1975 0.02113 0.01637 -0.0328 0.0030 1.0000
10.250 1.2174 0.02215 0.01752 -0.0320 0.0028 1.0000
10.500 1.2370 0.02315 0.01865 -0.0311 0.0027 1.0000
10.750 1.2563 0.02410 0.01973 -0.0302 0.0025 1.0000
11.000 1.2750 0.02510 0.02083 -0.0293 0.0024 1.0000
11.250 1.2915 0.02636 0.02224 -0.0282 0.0022 1.0000
11.500 1.3031 0.02826 0.02437 -0.0265 0.0021 1.0000
11.750 1.3025 0.03169 0.02822 -0.0236 0.0019 1.0000
12.000 1.3051 0.03432 0.03113 -0.0211 0.0019 1.0000
12.250 1.3033 0.03684 0.03388 -0.0182 0.0019 1.0000
12.500 1.2919 0.03995 0.03725 -0.0147 0.0019 1.0000
12.750 1.2736 0.04397 0.04155 -0.0118 0.0019 1.0000
13.000 1.2478 0.04929 0.04715 -0.0102 0.0019 1.0000
13.250 1.2120 0.05680 0.05494 -0.0109 0.0019 1.0000
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Polar data table (+)
Polar graphs
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