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RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il)
Reynolds number: 100,000
Max Cl/Cd: 35.95 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5213-il-100000-n5.txt
Download as CSV file: xf-rae5213-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5392   0.08990   0.08433  -0.0285   1.0000   0.0311
  -9.750  -0.5412   0.08497   0.07944  -0.0310   1.0000   0.0309
  -9.500  -0.5474   0.07872   0.07322  -0.0350   1.0000   0.0305
  -9.250  -0.5604   0.07194   0.06644  -0.0401   1.0000   0.0300
  -9.000  -0.5817   0.06584   0.06030  -0.0442   1.0000   0.0296
  -8.750  -0.6014   0.06107   0.05542  -0.0462   1.0000   0.0293
  -8.500  -0.6141   0.05632   0.05047  -0.0472   1.0000   0.0290
  -8.250  -0.6210   0.05182   0.04571  -0.0474   1.0000   0.0288
  -8.000  -0.6222   0.04770   0.04127  -0.0470   1.0000   0.0287
  -7.750  -0.6188   0.04391   0.03713  -0.0462   1.0000   0.0289
  -7.500  -0.6108   0.04069   0.03356  -0.0453   1.0000   0.0295
  -7.250  -0.6007   0.03742   0.02980  -0.0443   1.0000   0.0305
  -7.000  -0.5876   0.03453   0.02644  -0.0431   1.0000   0.0315
  -6.750  -0.5704   0.03286   0.02464  -0.0422   1.0000   0.0323
  -6.500  -0.5529   0.03086   0.02238  -0.0410   1.0000   0.0329
  -6.250  -0.5343   0.02894   0.02018  -0.0398   1.0000   0.0337
  -6.000  -0.5149   0.02715   0.01806  -0.0386   1.0000   0.0350
  -5.750  -0.4951   0.02581   0.01655  -0.0374   1.0000   0.0367
  -5.500  -0.4751   0.02476   0.01546  -0.0363   1.0000   0.0384
  -5.250  -0.4546   0.02354   0.01408  -0.0351   1.0000   0.0399
  -5.000  -0.4340   0.02243   0.01284  -0.0338   1.0000   0.0414
  -4.750  -0.4141   0.02164   0.01210  -0.0327   1.0000   0.0436
  -4.500  -0.3936   0.02085   0.01124  -0.0315   1.0000   0.0462
  -4.250  -0.3735   0.02003   0.01044  -0.0303   1.0000   0.0481
  -4.000  -0.3446   0.01934   0.00977  -0.0309   0.9969   0.0518
  -3.750  -0.3104   0.01859   0.00903  -0.0325   0.9915   0.0558
  -3.500  -0.2753   0.01794   0.00837  -0.0343   0.9860   0.0607
  -3.250  -0.2414   0.01734   0.00777  -0.0359   0.9799   0.0692
  -3.000  -0.2054   0.01670   0.00720  -0.0378   0.9746   0.0841
  -2.750  -0.1732   0.01579   0.00666  -0.0393   0.9676   0.1426
  -2.500  -0.1435   0.01403   0.00652  -0.0410   0.9626   0.4776
  -2.250  -0.1146   0.01415   0.00695  -0.0407   0.9543   0.5977
  -2.000  -0.0813   0.01455   0.00747  -0.0407   0.9487   0.6624
  -1.750  -0.0556   0.01484   0.00783  -0.0392   0.9397   0.7011
  -1.500  -0.0203   0.01490   0.00785  -0.0401   0.9345   0.7197
  -1.250   0.0108   0.01483   0.00768  -0.0408   0.9255   0.7279
  -1.000   0.0466   0.01474   0.00755  -0.0421   0.9194   0.7340
  -0.750   0.0777   0.01467   0.00743  -0.0426   0.9100   0.7412
  -0.500   0.1135   0.01457   0.00729  -0.0439   0.9031   0.7477
  -0.250   0.1437   0.01451   0.00722  -0.0442   0.8936   0.7540
   0.000   0.1786   0.01443   0.00710  -0.0454   0.8860   0.7610
   0.250   0.2077   0.01436   0.00706  -0.0453   0.8758   0.7669
   0.500   0.2417   0.01425   0.00695  -0.0461   0.8669   0.7733
   0.750   0.2712   0.01414   0.00685  -0.0460   0.8522   0.7801
   1.000   0.3016   0.01390   0.00661  -0.0455   0.8322   0.7859
   1.250   0.3296   0.01365   0.00631  -0.0444   0.8013   0.7927
   1.500   0.3571   0.01345   0.00602  -0.0432   0.7656   0.7992
   1.750   0.3838   0.01335   0.00586  -0.0421   0.7337   0.8062
   2.000   0.4109   0.01333   0.00579  -0.0414   0.7046   0.8139
   2.250   0.4362   0.01333   0.00576  -0.0403   0.6697   0.8212
   2.500   0.4615   0.01339   0.00573  -0.0392   0.6239   0.8304
   2.750   0.4846   0.01353   0.00566  -0.0376   0.5538   0.8390
   3.000   0.5047   0.01404   0.00564  -0.0357   0.4405   0.8495
   3.250   0.5217   0.01498   0.00590  -0.0338   0.3036   0.8621
   3.500   0.5410   0.01586   0.00629  -0.0325   0.2151   0.8778
   4.000   0.5933   0.01699   0.00714  -0.0323   0.1565   0.9328
   4.250   0.6230   0.01758   0.00765  -0.0331   0.1431   1.0000
   4.500   0.6486   0.01820   0.00819  -0.0330   0.1331   1.0000
   4.750   0.6740   0.01882   0.00876  -0.0329   0.1251   1.0000
   5.000   0.6987   0.01949   0.00937  -0.0326   0.1180   1.0000
   5.250   0.7237   0.02018   0.01005  -0.0323   0.1118   1.0000
   5.500   0.7485   0.02088   0.01069  -0.0320   0.1056   1.0000
   5.750   0.7730   0.02168   0.01147  -0.0316   0.1002   1.0000
   6.000   0.7978   0.02239   0.01219  -0.0313   0.0942   1.0000
   6.250   0.8218   0.02326   0.01298  -0.0309   0.0893   1.0000
   6.500   0.8466   0.02402   0.01384  -0.0306   0.0839   1.0000
   6.750   0.8703   0.02487   0.01462  -0.0302   0.0797   1.0000
   7.000   0.8948   0.02578   0.01569  -0.0297   0.0751   1.0000
   7.250   0.9183   0.02662   0.01653  -0.0293   0.0713   1.0000
   7.500   0.9418   0.02767   0.01767  -0.0288   0.0679   1.0000
   7.750   0.9650   0.02872   0.01885  -0.0283   0.0644   1.0000
   8.000   0.9873   0.02959   0.01969  -0.0278   0.0620   1.0000
   8.250   1.0095   0.03100   0.02136  -0.0271   0.0590   1.0000
   8.500   1.0311   0.03233   0.02283  -0.0264   0.0568   1.0000
   8.750   1.0521   0.03347   0.02402  -0.0258   0.0552   1.0000
   9.000   1.0718   0.03511   0.02585  -0.0250   0.0535   1.0000
   9.250   1.0890   0.03709   0.02817  -0.0240   0.0515   1.0000
   9.500   1.1061   0.03862   0.02988  -0.0230   0.0499   1.0000
   9.750   1.1233   0.03997   0.03133  -0.0221   0.0487   1.0000
  10.000   1.1391   0.04168   0.03313  -0.0212   0.0479   1.0000
  10.250   1.1438   0.04507   0.03707  -0.0193   0.0470   1.0000
  10.500   1.1448   0.04848   0.04092  -0.0174   0.0462   1.0000
  10.750   1.1412   0.05193   0.04475  -0.0153   0.0456   1.0000
  11.000   1.1319   0.05533   0.04847  -0.0130   0.0451   1.0000
  11.250   1.1166   0.05877   0.05219  -0.0106   0.0447   1.0000
  11.500   1.0952   0.06294   0.05662  -0.0092   0.0445   1.0000
  11.750   1.0651   0.06858   0.06254  -0.0097   0.0445   1.0000
  12.000   1.0142   0.07841   0.07268  -0.0146   0.0449   1.0000
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