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RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il)
Reynolds number: 200,000
Max Cl/Cd: 48.68 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5213-il-200000-n5.txt
Download as CSV file: xf-rae5213-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE(NPL) 5213 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5591   0.08960   0.08556  -0.0257   1.0000   0.0168
 -10.250  -0.5667   0.08329   0.07928  -0.0293   1.0000   0.0167
 -10.000  -0.5786   0.07528   0.07131  -0.0345   1.0000   0.0165
  -9.750  -0.6096   0.06329   0.05924  -0.0441   1.0000   0.0163
  -9.500  -0.6378   0.05658   0.05241  -0.0485   1.0000   0.0161
  -9.250  -0.6618   0.05168   0.04733  -0.0497   1.0000   0.0161
  -9.000  -0.6814   0.04573   0.04103  -0.0498   1.0000   0.0161
  -8.750  -0.6921   0.04015   0.03498  -0.0491   1.0000   0.0163
  -8.500  -0.6959   0.03482   0.02902  -0.0478   1.0000   0.0167
  -8.250  -0.6858   0.03222   0.02607  -0.0466   1.0000   0.0172
  -8.000  -0.6686   0.03136   0.02519  -0.0457   1.0000   0.0177
  -7.750  -0.6529   0.02988   0.02353  -0.0446   1.0000   0.0185
  -7.500  -0.6383   0.02750   0.02075  -0.0433   1.0000   0.0193
  -7.250  -0.6223   0.02508   0.01780  -0.0418   1.0000   0.0200
  -7.000  -0.6038   0.02386   0.01651  -0.0407   1.0000   0.0205
  -6.750  -0.5847   0.02282   0.01539  -0.0395   1.0000   0.0210
  -6.500  -0.5653   0.02186   0.01431  -0.0383   1.0000   0.0219
  -6.250  -0.5455   0.02080   0.01299  -0.0370   1.0000   0.0233
  -6.000  -0.5141   0.01983   0.01202  -0.0382   0.9969   0.0244
  -5.750  -0.4811   0.01887   0.01098  -0.0396   0.9932   0.0255
  -5.500  -0.4487   0.01790   0.00988  -0.0407   0.9891   0.0268
  -5.250  -0.4148   0.01714   0.00916  -0.0423   0.9855   0.0285
  -5.000  -0.3826   0.01650   0.00846  -0.0434   0.9807   0.0305
  -4.750  -0.3493   0.01576   0.00773  -0.0448   0.9764   0.0319
  -4.500  -0.3160   0.01519   0.00717  -0.0462   0.9719   0.0340
  -4.250  -0.2837   0.01464   0.00660  -0.0473   0.9662   0.0365
  -4.000  -0.2484   0.01412   0.00609  -0.0490   0.9625   0.0391
  -3.750  -0.2175   0.01366   0.00563  -0.0497   0.9556   0.0423
  -3.500  -0.1833   0.01324   0.00519  -0.0511   0.9507   0.0467
  -3.250  -0.1514   0.01281   0.00478  -0.0520   0.9443   0.0530
  -3.000  -0.1190   0.01235   0.00439  -0.0530   0.9379   0.0675
  -2.750  -0.0863   0.01173   0.00403  -0.0542   0.9321   0.1219
  -2.500  -0.0586   0.01068   0.00365  -0.0550   0.9234   0.2856
  -2.250  -0.0295   0.00980   0.00361  -0.0556   0.9168   0.4947
  -2.000  -0.0016   0.00973   0.00376  -0.0553   0.9074   0.5717
  -1.750   0.0291   0.00982   0.00395  -0.0552   0.9001   0.6240
  -1.500   0.0569   0.00995   0.00410  -0.0546   0.8896   0.6550
  -1.250   0.0863   0.00996   0.00411  -0.0544   0.8805   0.6681
  -1.000   0.1157   0.00994   0.00401  -0.0544   0.8701   0.6752
  -0.750   0.1442   0.00989   0.00395  -0.0542   0.8592   0.6797
  -0.500   0.1729   0.00985   0.00385  -0.0539   0.8459   0.6850
  -0.250   0.2011   0.00983   0.00375  -0.0535   0.8304   0.6906
   0.000   0.2283   0.00980   0.00368  -0.0530   0.8133   0.6951
   0.250   0.2553   0.00979   0.00360  -0.0523   0.7925   0.6998
   0.500   0.2815   0.00980   0.00350  -0.0514   0.7618   0.7050
   0.750   0.3077   0.00987   0.00340  -0.0506   0.7279   0.7103
   1.000   0.3336   0.00992   0.00337  -0.0498   0.6975   0.7144
   1.250   0.3599   0.01001   0.00336  -0.0491   0.6684   0.7193
   1.500   0.3861   0.01013   0.00336  -0.0485   0.6327   0.7246
   1.750   0.4112   0.01030   0.00337  -0.0476   0.5834   0.7292
   2.000   0.4343   0.01063   0.00340  -0.0464   0.5097   0.7339
   2.250   0.4554   0.01124   0.00354  -0.0451   0.4080   0.7393
   2.750   0.4979   0.01275   0.00410  -0.0432   0.2038   0.7495
   3.000   0.5218   0.01326   0.00439  -0.0426   0.1599   0.7554
   3.250   0.5472   0.01364   0.00467  -0.0422   0.1396   0.7619
   3.500   0.5723   0.01395   0.00495  -0.0416   0.1271   0.7675
   3.750   0.5974   0.01427   0.00525  -0.0411   0.1179   0.7741
   4.000   0.6228   0.01456   0.00557  -0.0406   0.1112   0.7813
   4.250   0.6474   0.01489   0.00590  -0.0400   0.1053   0.7894
   4.500   0.6721   0.01523   0.00626  -0.0394   0.1001   0.7982
   4.750   0.6965   0.01552   0.00661  -0.0387   0.0950   0.8079
   5.000   0.7202   0.01596   0.00704  -0.0380   0.0901   0.8193
   5.250   0.7450   0.01620   0.00739  -0.0373   0.0852   0.8342
   5.500   0.7684   0.01650   0.00774  -0.0365   0.0806   0.8557
   5.750   0.7922   0.01675   0.00813  -0.0356   0.0764   0.8976
   6.000   0.8222   0.01707   0.00851  -0.0362   0.0719   1.0000
   6.250   0.8474   0.01755   0.00897  -0.0359   0.0681   1.0000
   6.500   0.8728   0.01797   0.00942  -0.0356   0.0641   1.0000
   6.750   0.8973   0.01846   0.00988  -0.0352   0.0609   1.0000
   7.000   0.9220   0.01894   0.01041  -0.0348   0.0573   1.0000
   7.250   0.9459   0.01948   0.01092  -0.0343   0.0546   1.0000
   7.500   0.9697   0.02008   0.01159  -0.0337   0.0516   1.0000
   7.750   0.9931   0.02064   0.01216  -0.0332   0.0491   1.0000
   8.000   1.0158   0.02132   0.01287  -0.0325   0.0468   1.0000
   8.250   1.0385   0.02199   0.01361  -0.0319   0.0446   1.0000
   8.500   1.0605   0.02268   0.01430  -0.0312   0.0429   1.0000
   8.750   1.0819   0.02353   0.01522  -0.0304   0.0415   1.0000
   9.000   1.1031   0.02441   0.01620  -0.0295   0.0400   1.0000
   9.250   1.1239   0.02527   0.01713  -0.0287   0.0388   1.0000
   9.500   1.1440   0.02612   0.01802  -0.0278   0.0379   1.0000
   9.750   1.1631   0.02712   0.01908  -0.0269   0.0369   1.0000
  10.000   1.1823   0.02822   0.02035  -0.0259   0.0359   1.0000
  10.250   1.2005   0.02929   0.02156  -0.0248   0.0349   1.0000
  10.500   1.2178   0.03035   0.02272  -0.0237   0.0341   1.0000
  10.750   1.2342   0.03142   0.02386  -0.0225   0.0335   1.0000
  11.000   1.2494   0.03257   0.02509  -0.0213   0.0330   1.0000
  11.250   1.2629   0.03394   0.02655  -0.0199   0.0326   1.0000
  11.500   1.2736   0.03558   0.02843  -0.0182   0.0321   1.0000
  11.750   1.2808   0.03730   0.03038  -0.0161   0.0317   1.0000
  12.000   1.2853   0.03911   0.03242  -0.0139   0.0313   1.0000
  12.250   1.2877   0.04106   0.03457  -0.0118   0.0309   1.0000
  12.500   1.2879   0.04313   0.03684  -0.0098   0.0306   1.0000
  12.750   1.2864   0.04538   0.03928  -0.0082   0.0303   1.0000
  13.000   1.2833   0.04783   0.04191  -0.0069   0.0300   1.0000
  13.250   1.2785   0.05059   0.04486  -0.0061   0.0298   1.0000
  13.500   1.2725   0.05362   0.04805  -0.0058   0.0295   1.0000
  13.750   1.2641   0.05718   0.05178  -0.0061   0.0294   1.0000
  14.000   1.2543   0.06117   0.05594  -0.0071   0.0292   1.0000
  14.250   1.2385   0.06639   0.06136  -0.0091   0.0291   1.0000
  14.500   1.2199   0.07251   0.06769  -0.0123   0.0290   1.0000
  14.750   1.1702   0.08542   0.08099  -0.0210   0.0291   1.0000
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