PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Reynolds number: 200,000 Max Cl/Cd: 56.31 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-pfcm-il-200000-n5.txt Download as CSV file: xf-pfcm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5764 0.08687 0.08343 -0.0156 1.0000 0.0129
-8.750 -0.5782 0.08146 0.07807 -0.0196 1.0000 0.0129
-8.500 -0.5803 0.07488 0.07152 -0.0265 1.0000 0.0128
-8.250 -0.5818 0.06851 0.06508 -0.0325 1.0000 0.0128
-8.000 -0.5834 0.06281 0.05927 -0.0360 1.0000 0.0129
-7.750 -0.5818 0.05797 0.05428 -0.0382 1.0000 0.0132
-7.500 -0.5742 0.05504 0.05127 -0.0391 1.0000 0.0139
-7.250 -0.5694 0.04714 0.04295 -0.0403 1.0000 0.0130
-7.000 -0.5592 0.04227 0.03774 -0.0401 1.0000 0.0128
-6.750 -0.5483 0.03778 0.03288 -0.0394 1.0000 0.0128
-6.500 -0.5364 0.03359 0.02828 -0.0385 1.0000 0.0130
-6.250 -0.5220 0.03023 0.02455 -0.0374 1.0000 0.0133
-6.000 -0.5051 0.02768 0.02167 -0.0363 1.0000 0.0138
-5.750 -0.4867 0.02581 0.01952 -0.0351 1.0000 0.0146
-5.500 -0.4672 0.02467 0.01820 -0.0341 1.0000 0.0164
-5.250 -0.4472 0.02277 0.01594 -0.0328 1.0000 0.0176
-5.000 -0.4263 0.02084 0.01366 -0.0315 1.0000 0.0182
-4.750 -0.3934 0.01904 0.01150 -0.0325 0.9969 0.0191
-4.500 -0.3595 0.01798 0.01021 -0.0339 0.9934 0.0202
-4.250 -0.3279 0.01619 0.00829 -0.0351 0.9898 0.0223
-4.000 -0.2942 0.01507 0.00708 -0.0365 0.9865 0.0234
-3.750 -0.2616 0.01419 0.00614 -0.0378 0.9817 0.0249
-3.500 -0.2273 0.01346 0.00530 -0.0394 0.9777 0.0273
-3.250 -0.1945 0.01289 0.00461 -0.0407 0.9723 0.0305
-3.000 -0.1611 0.01232 0.00402 -0.0421 0.9670 0.0398
-2.750 -0.1289 0.01179 0.00353 -0.0432 0.9610 0.0627
-2.500 -0.0985 0.01063 0.00308 -0.0447 0.9547 0.2389
-2.250 -0.0724 0.00931 0.00297 -0.0451 0.9478 0.5539
-2.000 -0.0434 0.00903 0.00294 -0.0452 0.9406 0.6424
-1.750 -0.0175 0.00881 0.00299 -0.0444 0.9322 0.7295
-1.500 0.0094 0.00864 0.00294 -0.0437 0.9249 0.7832
-1.250 0.0363 0.00853 0.00284 -0.0432 0.9153 0.8033
-1.000 0.0640 0.00844 0.00274 -0.0430 0.9064 0.8200
-0.750 0.0917 0.00836 0.00264 -0.0427 0.8979 0.8373
-0.500 0.1182 0.00829 0.00258 -0.0422 0.8878 0.8572
-0.250 0.1458 0.00823 0.00253 -0.0418 0.8783 0.8809
0.250 0.2094 0.00814 0.00246 -0.0431 0.8596 0.9407
0.500 0.2460 0.00812 0.00243 -0.0450 0.8501 0.9747
0.750 0.2802 0.00812 0.00240 -0.0464 0.8402 1.0000
1.000 0.3067 0.00816 0.00241 -0.0462 0.8290 1.0000
1.250 0.3334 0.00821 0.00246 -0.0460 0.8173 1.0000
1.500 0.3602 0.00828 0.00251 -0.0458 0.8059 1.0000
1.750 0.3870 0.00835 0.00258 -0.0456 0.7944 1.0000
2.000 0.4138 0.00842 0.00266 -0.0453 0.7820 1.0000
2.250 0.4402 0.00851 0.00277 -0.0449 0.7655 1.0000
2.500 0.4652 0.00861 0.00278 -0.0440 0.7349 1.0000
2.750 0.4884 0.00879 0.00274 -0.0426 0.6774 1.0000
3.000 0.5119 0.00909 0.00279 -0.0414 0.6122 1.0000
3.250 0.5349 0.00953 0.00294 -0.0404 0.5315 1.0000
3.500 0.5500 0.01108 0.00332 -0.0386 0.2867 1.0000
3.750 0.5682 0.01265 0.00400 -0.0378 0.1035 1.0000
4.000 0.5917 0.01343 0.00454 -0.0373 0.0547 1.0000
4.250 0.6160 0.01411 0.00517 -0.0368 0.0390 1.0000
4.500 0.6408 0.01468 0.00588 -0.0364 0.0337 1.0000
4.750 0.6646 0.01540 0.00665 -0.0358 0.0292 1.0000
5.000 0.6880 0.01619 0.00751 -0.0352 0.0263 1.0000
5.250 0.7113 0.01701 0.00844 -0.0345 0.0247 1.0000
5.500 0.7342 0.01798 0.00951 -0.0337 0.0232 1.0000
5.750 0.7570 0.01909 0.01070 -0.0328 0.0219 1.0000
6.000 0.7804 0.02008 0.01180 -0.0322 0.0200 1.0000
6.250 0.8018 0.02190 0.01371 -0.0314 0.0178 1.0000
6.500 0.8254 0.02360 0.01560 -0.0306 0.0170 1.0000
6.750 0.8491 0.02533 0.01760 -0.0298 0.0163 1.0000
7.000 0.8720 0.02715 0.01973 -0.0289 0.0151 1.0000
7.250 0.8941 0.02857 0.02140 -0.0282 0.0134 1.0000
7.500 0.9142 0.03061 0.02375 -0.0272 0.0125 1.0000
7.750 0.9321 0.03293 0.02645 -0.0260 0.0119 1.0000
8.000 0.9473 0.03559 0.02944 -0.0247 0.0114 1.0000
8.250 0.9576 0.03916 0.03340 -0.0230 0.0110 1.0000
8.500 0.9612 0.04377 0.03848 -0.0208 0.0108 1.0000
8.750 0.9596 0.04873 0.04389 -0.0185 0.0107 1.0000
9.000 0.9523 0.05383 0.04937 -0.0162 0.0105 1.0000
9.250 0.9468 0.05804 0.05393 -0.0142 0.0103 1.0000
9.500 0.9349 0.06241 0.05855 -0.0122 0.0102 1.0000
9.750 0.9178 0.06673 0.06307 -0.0110 0.0101 1.0000
10.000 0.8993 0.07171 0.06820 -0.0118 0.0102 1.0000
10.250 0.8799 0.07745 0.07405 -0.0146 0.0104 1.0000
10.500 0.7669 0.07182 0.06864 -0.0055 0.0113 1.0000
10.750 0.7196 0.08863 0.08554 -0.0148 0.0122 1.0000
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Polar data table (+)
Polar graphs
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