PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=500,000 Ncrit=0
| Details | Polar file |
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Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Reynolds number: 500,000 Max Cl/Cd: 78.74 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-pfcm-il-500000.txt Download as CSV file: xf-pfcm-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4537 0.11976 0.11758 -0.0086 1.0000 0.0127
-11.250 -0.4569 0.11497 0.11280 -0.0096 1.0000 0.0130
-11.000 -0.4555 0.11138 0.10921 -0.0101 1.0000 0.0133
-10.750 -0.4536 0.10784 0.10568 -0.0108 1.0000 0.0136
-9.750 -0.5782 0.10190 0.09968 -0.0055 1.0000 0.0129
-9.500 -0.5797 0.09704 0.09483 -0.0078 1.0000 0.0131
-9.250 -0.5786 0.09287 0.09068 -0.0098 1.0000 0.0133
-5.750 -0.4669 0.01503 0.01123 -0.0363 0.9962 0.0226
-5.500 -0.4376 0.01288 0.00895 -0.0383 0.9940 0.0246
-5.000 -0.4114 0.01906 0.01376 -0.0350 0.9955 0.0187
-4.750 -0.3774 0.01709 0.01148 -0.0363 0.9934 0.0194
-4.500 -0.3434 0.01556 0.00969 -0.0376 0.9908 0.0211
-4.250 -0.3102 0.01342 0.00736 -0.0388 0.9887 0.0218
-4.000 -0.2755 0.01211 0.00597 -0.0405 0.9869 0.0227
-3.750 -0.2414 0.01133 0.00513 -0.0420 0.9839 0.0244
-3.500 -0.2067 0.01058 0.00433 -0.0436 0.9808 0.0256
-3.250 -0.1712 0.00994 0.00361 -0.0454 0.9779 0.0273
-3.000 -0.1374 0.00948 0.00309 -0.0467 0.9737 0.0308
-2.750 -0.1052 0.00888 0.00246 -0.0477 0.9682 0.0474
-2.500 -0.0760 0.00769 0.00206 -0.0488 0.9624 0.2533
-2.250 -0.0508 0.00648 0.00189 -0.0490 0.9548 0.5506
-2.000 -0.0245 0.00619 0.00188 -0.0486 0.9466 0.6406
-1.750 0.0018 0.00605 0.00184 -0.0480 0.9387 0.6900
-1.500 0.0276 0.00598 0.00179 -0.0474 0.9288 0.7162
-1.250 0.0528 0.00589 0.00178 -0.0466 0.9195 0.7533
-1.000 0.0770 0.00578 0.00177 -0.0454 0.9106 0.7946
-0.750 0.1022 0.00568 0.00172 -0.0446 0.9002 0.8181
-0.500 0.1278 0.00559 0.00167 -0.0439 0.8900 0.8396
-0.250 0.1529 0.00551 0.00163 -0.0431 0.8803 0.8617
0.000 0.1773 0.00543 0.00161 -0.0421 0.8702 0.8901
0.250 0.2025 0.00535 0.00160 -0.0411 0.8591 0.9288
0.500 0.2374 0.00532 0.00157 -0.0425 0.8492 0.9692
0.750 0.2775 0.00532 0.00154 -0.0453 0.8396 0.9993
1.000 0.3046 0.00537 0.00153 -0.0452 0.8281 1.0000
1.250 0.3315 0.00541 0.00154 -0.0451 0.8149 1.0000
1.500 0.3582 0.00547 0.00154 -0.0448 0.7987 1.0000
1.750 0.3848 0.00553 0.00155 -0.0445 0.7782 1.0000
2.000 0.4103 0.00565 0.00153 -0.0438 0.7464 1.0000
2.250 0.4360 0.00580 0.00156 -0.0433 0.7081 1.0000
2.500 0.4620 0.00598 0.00161 -0.0429 0.6700 1.0000
2.750 0.4878 0.00622 0.00169 -0.0424 0.6235 1.0000
3.000 0.5134 0.00652 0.00180 -0.0420 0.5699 1.0000
3.250 0.5374 0.00705 0.00199 -0.0415 0.4763 1.0000
3.500 0.5560 0.00860 0.00250 -0.0406 0.2380 1.0000
3.750 0.5760 0.01009 0.00315 -0.0399 0.0570 1.0000
4.000 0.6012 0.01072 0.00370 -0.0395 0.0344 1.0000
4.250 0.6261 0.01137 0.00438 -0.0390 0.0289 1.0000
4.500 0.6506 0.01208 0.00520 -0.0384 0.0272 1.0000
4.750 0.6756 0.01265 0.00584 -0.0380 0.0259 1.0000
5.000 0.7001 0.01335 0.00661 -0.0374 0.0243 1.0000
5.250 0.7247 0.01400 0.00731 -0.0369 0.0222 1.0000
5.500 0.7485 0.01487 0.00823 -0.0362 0.0209 1.0000
5.750 0.7719 0.01593 0.00939 -0.0354 0.0197 1.0000
6.000 0.7915 0.01952 0.01318 -0.0340 0.0175 1.0000
6.250 0.8176 0.01958 0.01334 -0.0337 0.0166 1.0000
6.500 0.8421 0.02105 0.01500 -0.0329 0.0157 1.0000
6.750 0.8654 0.02319 0.01741 -0.0319 0.0149 1.0000
7.000 0.8866 0.02616 0.02074 -0.0305 0.0144 1.0000
7.250 0.9081 0.02759 0.02237 -0.0297 0.0131 1.0000
7.500 0.9298 0.02800 0.02279 -0.0295 0.0119 1.0000
7.750 0.9457 0.03111 0.02627 -0.0279 0.0116 1.0000
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Polar data table (+)
Polar graphs
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