RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 100,000 Max Cl/Cd: 47.68 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5212-il-100000.txt Download as CSV file: xf-rae5212-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5212 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5366 0.09149 0.08655 -0.0441 1.0000 0.1538
-9.000 -0.4659 0.09059 0.08553 -0.0348 1.0000 0.1624
-8.750 -0.5064 0.08623 0.08134 -0.0385 1.0000 0.1686
-8.500 -0.4847 0.08392 0.07903 -0.0348 1.0000 0.1756
-8.250 -0.5097 0.08059 0.07583 -0.0352 1.0000 0.1828
-8.000 -0.5620 0.07613 0.07152 -0.0365 1.0000 0.1839
-7.750 -0.5343 0.07513 0.07056 -0.0313 1.0000 0.1959
-7.500 -0.5869 0.07036 0.06584 -0.0330 1.0000 0.1993
-7.000 -0.6615 0.04950 0.04274 -0.0361 1.0000 0.0942
-6.750 -0.6465 0.04470 0.03813 -0.0353 1.0000 0.0901
-6.500 -0.6369 0.04031 0.03281 -0.0331 1.0000 0.0795
-6.250 -0.6221 0.03701 0.02930 -0.0319 1.0000 0.0776
-6.000 -0.6055 0.03423 0.02617 -0.0306 1.0000 0.0760
-5.750 -0.5869 0.03189 0.02346 -0.0293 1.0000 0.0752
-5.500 -0.5671 0.03013 0.02139 -0.0281 1.0000 0.0766
-5.250 -0.5464 0.02878 0.01969 -0.0268 1.0000 0.0790
-5.000 -0.5250 0.02753 0.01812 -0.0256 1.0000 0.0803
-4.750 -0.5033 0.02566 0.01623 -0.0246 1.0000 0.0825
-4.500 -0.4830 0.02462 0.01524 -0.0237 1.0000 0.0874
-4.250 -0.4619 0.02377 0.01428 -0.0225 1.0000 0.0920
-4.000 -0.4414 0.02264 0.01320 -0.0212 1.0000 0.0968
-3.750 -0.4215 0.02192 0.01256 -0.0201 1.0000 0.1050
-3.500 -0.4020 0.02107 0.01185 -0.0189 1.0000 0.1144
-3.250 -0.3823 0.02034 0.01123 -0.0178 1.0000 0.1301
-3.000 -0.3621 0.01937 0.01050 -0.0171 1.0000 0.1672
-2.750 -0.3528 0.01772 0.01113 -0.0137 1.0000 0.6035
-2.500 -0.3397 0.01855 0.01197 -0.0099 1.0000 0.6569
-2.250 -0.3258 0.01910 0.01251 -0.0066 1.0000 0.6887
-2.000 -0.3112 0.01954 0.01291 -0.0036 0.9998 0.7165
-1.750 -0.2840 0.02033 0.01372 -0.0025 0.9938 0.7469
-1.500 -0.2633 0.02090 0.01434 0.0002 0.9871 0.7808
-1.250 -0.2453 0.02132 0.01481 0.0035 0.9805 0.8126
-1.000 -0.2218 0.02153 0.01501 0.0049 0.9739 0.8327
-0.750 -0.1916 0.02162 0.01500 0.0038 0.9670 0.8422
-0.500 -0.1566 0.02180 0.01508 0.0017 0.9607 0.8496
-0.250 -0.1271 0.02186 0.01508 0.0007 0.9531 0.8577
0.000 -0.0891 0.02208 0.01523 -0.0019 0.9464 0.8649
0.250 -0.0602 0.02212 0.01522 -0.0028 0.9378 0.8729
0.500 -0.0183 0.02237 0.01544 -0.0060 0.9310 0.8805
0.750 0.0089 0.02239 0.01544 -0.0066 0.9215 0.8892
1.000 0.0518 0.02261 0.01564 -0.0098 0.9146 0.8972
1.250 0.0819 0.02264 0.01569 -0.0108 0.9045 0.9069
1.500 0.1203 0.02274 0.01582 -0.0132 0.8953 0.9162
1.750 0.1676 0.02278 0.01589 -0.0170 0.8863 0.9261
2.000 0.2096 0.02275 0.01592 -0.0198 0.8742 0.9369
2.250 0.2638 0.02259 0.01584 -0.0245 0.8629 0.9465
2.500 0.3288 0.02212 0.01545 -0.0305 0.8532 0.9542
2.750 0.4014 0.02068 0.01409 -0.0363 0.8369 0.9576
3.000 0.4731 0.01868 0.01218 -0.0410 0.8153 0.9595
3.250 0.5313 0.01748 0.01107 -0.0447 0.7961 0.9652
3.500 0.5856 0.01647 0.01014 -0.0480 0.7744 0.9718
3.750 0.6344 0.01571 0.00946 -0.0507 0.7444 0.9805
4.000 0.6806 0.01510 0.00888 -0.0531 0.7013 0.9912
4.250 0.7017 0.01476 0.00844 -0.0514 0.6402 1.0000
4.500 0.7047 0.01478 0.00795 -0.0463 0.5271 1.0000
4.750 0.7001 0.01635 0.00817 -0.0408 0.3352 1.0000
5.000 0.7064 0.01811 0.00902 -0.0379 0.2399 1.0000
5.250 0.7247 0.01933 0.00983 -0.0368 0.2074 1.0000
5.500 0.7477 0.02041 0.01064 -0.0363 0.1901 1.0000
5.750 0.7733 0.02132 0.01145 -0.0362 0.1774 1.0000
6.000 0.8004 0.02231 0.01236 -0.0363 0.1678 1.0000
6.250 0.8296 0.02347 0.01332 -0.0368 0.1606 1.0000
6.500 0.8585 0.02454 0.01447 -0.0371 0.1548 1.0000
6.750 0.8865 0.02558 0.01549 -0.0373 0.1488 1.0000
7.000 0.9178 0.02717 0.01692 -0.0383 0.1439 1.0000
7.250 0.9447 0.02834 0.01831 -0.0381 0.1406 1.0000
7.500 0.9712 0.02966 0.01978 -0.0380 0.1370 1.0000
7.750 0.9968 0.03098 0.02118 -0.0378 0.1332 1.0000
8.000 1.0249 0.03309 0.02322 -0.0384 0.1298 1.0000
8.250 1.0461 0.03479 0.02526 -0.0374 0.1280 1.0000
8.500 1.0657 0.03663 0.02745 -0.0361 0.1264 1.0000
8.750 1.0832 0.03863 0.02980 -0.0347 0.1245 1.0000
9.000 1.0994 0.04069 0.03216 -0.0333 0.1223 1.0000
9.250 1.1151 0.04284 0.03458 -0.0319 0.1202 1.0000
9.500 1.1282 0.04543 0.03745 -0.0302 0.1192 1.0000
9.750 1.1393 0.04818 0.04049 -0.0285 0.1183 1.0000
10.000 1.1573 0.05081 0.04317 -0.0279 0.1165 1.0000
10.250 1.1672 0.05519 0.04770 -0.0269 0.1149 1.0000
10.500 1.1654 0.05883 0.05170 -0.0242 0.1146 1.0000
10.750 1.1631 0.06287 0.05605 -0.0218 0.1146 1.0000
11.000 1.1567 0.06706 0.06054 -0.0192 0.1147 1.0000
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Polar data table (+)
Polar graphs
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