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RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il)
Reynolds number: 500,000
Max Cl/Cd: 65.91 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5213-il-500000.txt
Download as CSV file: xf-rae5213-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5413   0.09725   0.09470  -0.0245   1.0000   0.0235
 -10.500  -0.5380   0.09436   0.09183  -0.0249   1.0000   0.0236
 -10.250  -0.5365   0.09070   0.08819  -0.0263   1.0000   0.0237
 -10.000  -0.5361   0.08672   0.08423  -0.0281   1.0000   0.0239
  -9.750  -0.5366   0.08266   0.08020  -0.0300   1.0000   0.0241
  -9.500  -0.5415   0.07717   0.07473  -0.0335   1.0000   0.0242
  -9.250  -0.5715   0.06517   0.06268  -0.0445   1.0000   0.0241
  -9.000  -0.6019   0.05933   0.05677  -0.0481   1.0000   0.0241
  -8.750  -0.6172   0.05507   0.05238  -0.0491   1.0000   0.0242
  -8.500  -0.7016   0.03321   0.02903  -0.0475   1.0000   0.0168
  -8.250  -0.6959   0.02965   0.02515  -0.0458   1.0000   0.0167
  -8.000  -0.6881   0.02615   0.02117  -0.0439   1.0000   0.0168
  -7.750  -0.6766   0.02323   0.01781  -0.0421   1.0000   0.0171
  -7.500  -0.6598   0.02183   0.01634  -0.0408   1.0000   0.0175
  -7.250  -0.6415   0.02113   0.01563  -0.0395   1.0000   0.0179
  -7.000  -0.6236   0.02007   0.01445  -0.0380   1.0000   0.0184
  -6.750  -0.6046   0.01888   0.01306  -0.0367   0.9999   0.0191
  -6.500  -0.5694   0.01778   0.01162  -0.0383   0.9977   0.0200
  -6.250  -0.5364   0.01640   0.01027  -0.0399   0.9956   0.0210
  -6.000  -0.5015   0.01570   0.00953  -0.0416   0.9933   0.0222
  -5.750  -0.4672   0.01493   0.00861  -0.0430   0.9903   0.0237
  -5.500  -0.4325   0.01423   0.00798  -0.0448   0.9877   0.0252
  -5.250  -0.3954   0.01381   0.00746  -0.0467   0.9856   0.0270
  -5.000  -0.3624   0.01298   0.00671  -0.0481   0.9821   0.0289
  -4.750  -0.3275   0.01245   0.00615  -0.0496   0.9786   0.0306
  -4.500  -0.2914   0.01174   0.00546  -0.0515   0.9761   0.0322
  -4.250  -0.2533   0.01130   0.00504  -0.0537   0.9743   0.0345
  -4.000  -0.2210   0.01083   0.00456  -0.0547   0.9688   0.0366
  -3.750  -0.1852   0.01039   0.00415  -0.0564   0.9651   0.0389
  -3.500  -0.1487   0.00998   0.00375  -0.0581   0.9621   0.0422
  -3.250  -0.1190   0.00966   0.00344  -0.0584   0.9544   0.0460
  -3.000  -0.0852   0.00929   0.00309  -0.0595   0.9495   0.0538
  -2.750  -0.0575   0.00857   0.00269  -0.0596   0.9401   0.1198
  -2.500  -0.0319   0.00705   0.00222  -0.0601   0.9313   0.4033
  -2.250  -0.0057   0.00659   0.00218  -0.0597   0.9206   0.5322
  -2.000   0.0216   0.00652   0.00219  -0.0592   0.9098   0.5722
  -1.750   0.0494   0.00651   0.00217  -0.0587   0.8982   0.5963
  -1.500   0.0765   0.00653   0.00215  -0.0580   0.8847   0.6143
  -1.250   0.1034   0.00660   0.00221  -0.0574   0.8717   0.6346
  -1.000   0.1305   0.00671   0.00231  -0.0568   0.8599   0.6539
  -0.750   0.1570   0.00680   0.00239  -0.0559   0.8455   0.6690
  -0.500   0.1835   0.00684   0.00237  -0.0552   0.8265   0.6783
  -0.250   0.2100   0.00686   0.00231  -0.0545   0.8044   0.6832
   0.000   0.2371   0.00690   0.00226  -0.0540   0.7840   0.6880
   0.250   0.2645   0.00696   0.00223  -0.0536   0.7652   0.6924
   0.500   0.2915   0.00697   0.00220  -0.0531   0.7463   0.6966
   0.750   0.3188   0.00702   0.00220  -0.0527   0.7281   0.7009
   1.000   0.3459   0.00710   0.00220  -0.0523   0.7063   0.7056
   1.250   0.3729   0.00720   0.00221  -0.0519   0.6806   0.7101
   1.500   0.3991   0.00728   0.00221  -0.0513   0.6467   0.7143
   1.750   0.4244   0.00748   0.00224  -0.0505   0.5962   0.7188
   2.000   0.4480   0.00788   0.00230  -0.0496   0.5121   0.7236
   2.250   0.4694   0.00864   0.00250  -0.0485   0.3858   0.7281
   2.500   0.4897   0.00960   0.00282  -0.0474   0.2344   0.7325
   2.750   0.5131   0.01026   0.00310  -0.0468   0.1558   0.7373
   3.000   0.5390   0.01062   0.00333  -0.0464   0.1334   0.7424
   3.250   0.5654   0.01085   0.00354  -0.0461   0.1224   0.7473
   3.500   0.5915   0.01111   0.00378  -0.0457   0.1143   0.7526
   3.750   0.6180   0.01134   0.00399  -0.0454   0.1080   0.7581
   4.000   0.6439   0.01164   0.00428  -0.0450   0.1014   0.7639
   4.250   0.6702   0.01181   0.00448  -0.0446   0.0960   0.7701
   4.500   0.6952   0.01221   0.00484  -0.0441   0.0902   0.7771
   4.750   0.7219   0.01233   0.00504  -0.0438   0.0864   0.7840
   5.000   0.7477   0.01256   0.00528  -0.0434   0.0821   0.7921
   5.250   0.7726   0.01290   0.00564  -0.0428   0.0781   0.8012
   5.500   0.7987   0.01305   0.00586  -0.0424   0.0744   0.8127
   5.750   0.8231   0.01332   0.00616  -0.0418   0.0705   0.8268
   6.000   0.8479   0.01347   0.00642  -0.0411   0.0670   0.8467
   6.250   0.8699   0.01349   0.00659  -0.0397   0.0634   0.8905
   6.500   0.9005   0.01373   0.00692  -0.0404   0.0593   1.0000
   6.750   0.9267   0.01406   0.00720  -0.0402   0.0556   1.0000
   7.000   0.9519   0.01448   0.00763  -0.0398   0.0519   1.0000
   7.250   0.9765   0.01493   0.00803  -0.0394   0.0488   1.0000
   7.500   1.0008   0.01543   0.00856  -0.0388   0.0460   1.0000
   7.750   1.0252   0.01588   0.00899  -0.0383   0.0436   1.0000
   8.000   1.0478   0.01655   0.00966  -0.0375   0.0417   1.0000
   8.250   1.0717   0.01704   0.01020  -0.0369   0.0400   1.0000
   8.500   1.0950   0.01758   0.01075  -0.0362   0.0386   1.0000
   8.750   1.1155   0.01850   0.01163  -0.0353   0.0373   1.0000
   9.000   1.1383   0.01909   0.01231  -0.0345   0.0365   1.0000
   9.250   1.1606   0.01975   0.01305  -0.0337   0.0356   1.0000
   9.500   1.1824   0.02042   0.01377  -0.0329   0.0347   1.0000
   9.750   1.2037   0.02113   0.01450  -0.0320   0.0340   1.0000
  10.000   1.2241   0.02193   0.01531  -0.0311   0.0333   1.0000
  10.250   1.2425   0.02316   0.01658  -0.0300   0.0326   1.0000
  10.500   1.2627   0.02393   0.01748  -0.0290   0.0321   1.0000
  10.750   1.2819   0.02484   0.01850  -0.0279   0.0316   1.0000
  11.000   1.3003   0.02583   0.01959  -0.0268   0.0312   1.0000
  11.250   1.3178   0.02684   0.02071  -0.0256   0.0307   1.0000
  11.500   1.3344   0.02788   0.02185  -0.0243   0.0303   1.0000
  11.750   1.3500   0.02895   0.02300  -0.0229   0.0300   1.0000
  12.000   1.3645   0.03006   0.02419  -0.0214   0.0296   1.0000
  12.250   1.3766   0.03128   0.02549  -0.0197   0.0294   1.0000
  12.500   1.3866   0.03268   0.02696  -0.0177   0.0291   1.0000
  12.750   1.3940   0.03461   0.02899  -0.0158   0.0288   1.0000
  13.000   1.3964   0.03671   0.03127  -0.0134   0.0286   1.0000
  13.250   1.3971   0.03844   0.03318  -0.0109   0.0285   1.0000
  13.500   1.3950   0.04043   0.03538  -0.0086   0.0283   1.0000
  13.750   1.3907   0.04277   0.03792  -0.0067   0.0282   1.0000
  14.000   1.3834   0.04551   0.04088  -0.0052   0.0281   1.0000
  14.250   1.3735   0.04876   0.04433  -0.0042   0.0281   1.0000
  14.500   1.3603   0.05253   0.04832  -0.0040   0.0280   1.0000
  14.750   1.3442   0.05703   0.05304  -0.0046   0.0279   1.0000
  15.000   1.3245   0.06244   0.05867  -0.0062   0.0280   1.0000
  15.250   1.2998   0.06911   0.06557  -0.0093   0.0280   1.0000
  15.500   1.2707   0.07732   0.07401  -0.0142   0.0280   1.0000
  15.750   1.2339   0.08812   0.08506  -0.0215   0.0281   1.0000
  16.000   1.1781   0.10484   0.10205  -0.0335   0.0284   1.0000
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