RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 50,000 Max Cl/Cd: 31.21 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5212-il-50000.txt Download as CSV file: xf-rae5212-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4008 0.10114 0.09393 -0.0127 1.0000 0.3952
-8.250 -0.4038 0.09916 0.09202 -0.0111 1.0000 0.4103
-7.750 -0.5620 0.07456 0.06794 -0.0359 1.0000 0.1975
-7.500 -0.6147 0.06608 0.05918 -0.0396 1.0000 0.1673
-7.250 -0.6324 0.06037 0.05303 -0.0398 1.0000 0.1521
-7.000 -0.6283 0.05631 0.04886 -0.0386 1.0000 0.1477
-6.750 -0.6339 0.05187 0.04351 -0.0379 1.0000 0.1376
-6.500 -0.6221 0.04822 0.03971 -0.0367 1.0000 0.1353
-6.250 -0.6100 0.04484 0.03600 -0.0355 1.0000 0.1325
-6.000 -0.5958 0.04180 0.03255 -0.0343 1.0000 0.1311
-5.750 -0.5793 0.03928 0.02962 -0.0331 1.0000 0.1325
-5.500 -0.5607 0.03699 0.02691 -0.0320 1.0000 0.1346
-5.250 -0.5400 0.03487 0.02436 -0.0308 1.0000 0.1362
-5.000 -0.5185 0.03292 0.02208 -0.0296 1.0000 0.1394
-4.750 -0.4972 0.03119 0.02042 -0.0284 1.0000 0.1465
-4.500 -0.4741 0.02985 0.01879 -0.0271 1.0000 0.1533
-4.250 -0.4524 0.02841 0.01751 -0.0255 1.0000 0.1637
-4.000 -0.4316 0.02721 0.01639 -0.0237 1.0000 0.1776
-3.750 -0.4123 0.02604 0.01533 -0.0219 1.0000 0.1980
-3.500 -0.3935 0.02448 0.01413 -0.0205 1.0000 0.2364
-3.250 -0.3905 0.02231 0.01455 -0.0150 1.0000 0.5612
-3.000 -0.3989 0.02428 0.01661 -0.0028 1.0000 0.6957
-2.750 -0.4006 0.02502 0.01731 0.0062 1.0000 0.7488
-2.500 -0.4004 0.02531 0.01756 0.0144 1.0000 0.7879
-2.250 -0.3981 0.02533 0.01751 0.0214 1.0000 0.8260
-2.000 -0.2108 0.02856 0.01995 0.0055 1.0000 0.9548
-1.750 -0.1623 0.02819 0.01934 -0.0001 1.0000 0.9674
-1.500 -0.1193 0.02786 0.01881 -0.0050 1.0000 0.9788
-1.250 -0.0785 0.02758 0.01837 -0.0096 1.0000 0.9898
-1.000 -0.0412 0.02742 0.01807 -0.0137 1.0000 1.0000
-0.750 -0.0431 0.02716 0.01779 -0.0108 1.0000 1.0000
-0.500 -0.0456 0.02689 0.01751 -0.0079 1.0000 1.0000
-0.250 -0.0488 0.02659 0.01718 -0.0049 1.0000 1.0000
0.000 -0.0529 0.02624 0.01683 -0.0018 1.0000 1.0000
0.250 -0.0579 0.02584 0.01642 0.0015 1.0000 1.0000
0.500 -0.0629 0.02539 0.01596 0.0047 1.0000 1.0000
0.750 -0.0651 0.02498 0.01553 0.0073 1.0000 1.0000
1.000 -0.0576 0.02484 0.01534 0.0084 1.0000 1.0000
1.250 -0.0421 0.02498 0.01541 0.0082 1.0000 1.0000
1.500 -0.0227 0.02530 0.01566 0.0074 1.0000 1.0000
1.750 -0.0014 0.02575 0.01606 0.0063 1.0000 1.0000
2.000 0.0204 0.02631 0.01656 0.0051 1.0000 1.0000
2.250 0.0421 0.02696 0.01718 0.0039 1.0000 1.0000
2.500 0.0635 0.02770 0.01788 0.0028 1.0000 1.0000
2.750 0.0848 0.02853 0.01870 0.0016 0.9997 1.0000
3.000 0.1533 0.03083 0.02105 -0.0081 0.9745 1.0000
3.250 0.2122 0.03245 0.02274 -0.0154 0.9486 1.0000
3.500 0.2674 0.03367 0.02405 -0.0215 0.9216 1.0000
3.750 0.3239 0.03456 0.02509 -0.0271 0.8927 1.0000
4.000 0.3874 0.03488 0.02558 -0.0326 0.8588 1.0000
4.250 0.4716 0.03356 0.02457 -0.0384 0.8156 1.0000
4.500 0.5748 0.02951 0.02094 -0.0433 0.7700 1.0000
4.750 0.6391 0.02631 0.01809 -0.0433 0.7253 1.0000
5.000 0.6848 0.02326 0.01522 -0.0400 0.6500 1.0000
5.250 0.7101 0.02275 0.01299 -0.0335 0.4101 1.0000
5.500 0.7288 0.02505 0.01427 -0.0318 0.3237 1.0000
5.750 0.7628 0.02687 0.01562 -0.0328 0.2833 1.0000
6.000 0.7969 0.02842 0.01703 -0.0337 0.2588 1.0000
6.250 0.8332 0.03011 0.01865 -0.0350 0.2437 1.0000
6.500 0.8656 0.03186 0.02040 -0.0358 0.2325 1.0000
6.750 0.8967 0.03366 0.02210 -0.0365 0.2222 1.0000
7.000 0.9202 0.03545 0.02424 -0.0358 0.2155 1.0000
7.250 0.9465 0.03745 0.02639 -0.0357 0.2100 1.0000
7.500 0.9715 0.03976 0.02879 -0.0356 0.2049 1.0000
7.750 0.9870 0.04194 0.03144 -0.0340 0.2005 1.0000
8.000 1.0036 0.04437 0.03419 -0.0327 0.1970 1.0000
8.250 1.0188 0.04713 0.03726 -0.0314 0.1951 1.0000
8.500 1.0336 0.04999 0.04036 -0.0302 0.1930 1.0000
8.750 1.0528 0.05322 0.04365 -0.0297 0.1900 1.0000
9.000 1.0523 0.05659 0.04750 -0.0271 0.1892 1.0000
9.250 1.0502 0.06037 0.05167 -0.0248 0.1889 1.0000
9.500 1.0508 0.06457 0.05614 -0.0231 0.1897 1.0000
9.750 0.9969 0.07023 0.06243 -0.0184 0.1950 1.0000
10.000 0.9456 0.07651 0.06889 -0.0156 0.2001 1.0000
10.250 0.9253 0.08248 0.07493 -0.0155 0.2039 1.0000
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Polar data table (+)
Polar graphs
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