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RAF 69 AIRFOIL (raf69-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAF 69 AIRFOIL (raf69-il)
Reynolds number: 50,000
Max Cl/Cd: 18.75 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf69-il-50000-n5.txt
Download as CSV file: xf-raf69-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 69 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4987   0.09512   0.08615  -0.0606   1.0000   0.1729
 -12.500  -0.6753   0.06609   0.05698  -0.0709   1.0000   0.1879
 -12.250  -0.5883   0.07432   0.06540  -0.0661   1.0000   0.1906
 -12.000  -0.5823   0.07317   0.06428  -0.0649   1.0000   0.1946
 -11.750  -0.7196   0.05795   0.04888  -0.0667   1.0000   0.1997
 -11.500  -0.7839   0.05316   0.04395  -0.0623   1.0000   0.2018
 -11.250  -0.8367   0.05046   0.04112  -0.0559   1.0000   0.2034
 -11.000  -0.8365   0.05011   0.04088  -0.0525   1.0000   0.2067
 -10.750  -0.8516   0.04945   0.04026  -0.0477   1.0000   0.2097
 -10.500  -0.8801   0.04850   0.03928  -0.0414   1.0000   0.2122
 -10.250  -0.8953   0.04702   0.03763  -0.0377   0.9950   0.2168
 -10.000  -0.8775   0.04573   0.03621  -0.0385   0.9860   0.2236
  -9.750  -0.8536   0.04488   0.03530  -0.0396   0.9783   0.2311
  -9.500  -0.8430   0.04335   0.03354  -0.0394   0.9683   0.2386
  -9.250  -0.8152   0.04292   0.03315  -0.0403   0.9608   0.2460
  -9.000  -0.8030   0.04145   0.03137  -0.0401   0.9520   0.2548
  -8.750  -0.7760   0.04119   0.03123  -0.0404   0.9441   0.2617
  -8.500  -0.7573   0.04005   0.02985  -0.0407   0.9364   0.2711
  -8.250  -0.7356   0.03967   0.02953  -0.0402   0.9279   0.2781
  -8.000  -0.7131   0.03886   0.02856  -0.0405   0.9208   0.2874
  -7.750  -0.6936   0.03836   0.02805  -0.0398   0.9127   0.2951
  -7.500  -0.6710   0.03779   0.02739  -0.0397   0.9052   0.3041
  -7.250  -0.6403   0.03719   0.02673  -0.0409   0.9000   0.3136
  -7.000  -0.6296   0.03684   0.02635  -0.0386   0.8901   0.3214
  -6.750  -0.6013   0.03624   0.02566  -0.0393   0.8842   0.3313
  -6.500  -0.5822   0.03593   0.02533  -0.0383   0.8764   0.3402
  -6.250  -0.5634   0.03547   0.02479  -0.0373   0.8685   0.3495
  -6.000  -0.5292   0.03505   0.02435  -0.0387   0.8636   0.3607
  -5.750  -0.5183   0.03481   0.02408  -0.0362   0.8542   0.3694
  -5.500  -0.4936   0.03449   0.02372  -0.0360   0.8474   0.3802
  -5.250  -0.4571   0.03411   0.02334  -0.0376   0.8429   0.3925
  -5.000  -0.4539   0.03395   0.02311  -0.0338   0.8322   0.4024
  -4.750  -0.4231   0.03373   0.02294  -0.0343   0.8262   0.4142
  -4.500  -0.3866   0.03333   0.02251  -0.0358   0.8219   0.4285
  -4.250  -0.3860   0.03338   0.02254  -0.0315   0.8103   0.4388
  -4.000  -0.3531   0.03313   0.02232  -0.0322   0.8049   0.4529
  -3.750  -0.3369   0.03302   0.02219  -0.0304   0.7967   0.4661
  -3.500  -0.3194   0.03292   0.02207  -0.0287   0.7883   0.4803
  -3.250  -0.2833   0.03270   0.02189  -0.0297   0.7836   0.4964
  -3.000  -0.2762   0.03285   0.02208  -0.0264   0.7733   0.5087
  -2.750  -0.2500   0.03271   0.02192  -0.0259   0.7667   0.5252
  -2.500  -0.2133   0.03245   0.02165  -0.0270   0.7625   0.5435
  -2.250  -0.2123   0.03283   0.02210  -0.0226   0.7507   0.5556
  -2.000  -0.1792   0.03272   0.02201  -0.0231   0.7454   0.5727
  -1.750  -0.1648   0.03289   0.02219  -0.0207   0.7367   0.5880
  -1.500  -0.1461   0.03296   0.02227  -0.0190   0.7286   0.6046
  -1.250  -0.1105   0.03282   0.02213  -0.0197   0.7242   0.6232
  -1.000  -0.1072   0.03331   0.02268  -0.0157   0.7129   0.6366
  -0.750  -0.0756   0.03331   0.02270  -0.0157   0.7070   0.6536
  -0.500  -0.0356   0.03317   0.02255  -0.0169   0.7033   0.6713
  -0.250  -0.0440   0.03378   0.02319  -0.0114   0.6903   0.6859
   0.000  -0.0081   0.03365   0.02305  -0.0120   0.6856   0.7039
   0.250  -0.0079   0.03419   0.02361  -0.0077   0.6746   0.7195
   0.500   0.0221   0.03424   0.02368  -0.0074   0.6684   0.7357
   0.750   0.0650   0.03404   0.02346  -0.0090   0.6647   0.7524
   1.000   0.0538   0.03479   0.02426  -0.0033   0.6517   0.7683
   1.250   0.0916   0.03463   0.02408  -0.0041   0.6471   0.7852
   1.750   0.1220   0.03529   0.02478  -0.0001   0.6299   0.8195
   2.000   0.1790   0.03508   0.02457  -0.0039   0.6264   0.8327
   2.250   0.1787   0.03617   0.02573  -0.0006   0.6140   0.8493
   2.500   0.2277   0.03600   0.02553  -0.0034   0.6092   0.8634
   2.750   0.2876   0.03567   0.02517  -0.0079   0.6056   0.8756
   3.000   0.2950   0.03696   0.02655  -0.0063   0.5926   0.8911
   3.250   0.3566   0.03654   0.02609  -0.0111   0.5887   0.9017
   3.500   0.3694   0.03774   0.02735  -0.0105   0.5766   0.9177
   3.750   0.4357   0.03739   0.02698  -0.0165   0.5715   0.9250
   4.250   0.5077   0.03807   0.02770  -0.0208   0.5543   0.9506
   4.500   0.5801   0.03715   0.02674  -0.0272   0.5500   0.9565
   4.750   0.5898   0.03850   0.02818  -0.0268   0.5372   0.9734
   5.000   0.6550   0.03758   0.02723  -0.0322   0.5321   0.9809
   5.250   0.6732   0.03875   0.02848  -0.0332   0.5201   0.9969
   5.500   0.7139   0.03808   0.02778  -0.0350   0.5143   1.0000
   5.750   0.6382   0.04010   0.02977  -0.0219   0.5033   1.0000
   6.000   0.6461   0.03993   0.02955  -0.0188   0.4971   1.0000
   6.500   0.6210   0.04186   0.03136  -0.0092   0.4795   1.0000
   6.750   0.6619   0.04072   0.03015  -0.0095   0.4758   1.0000
   7.000   0.6174   0.04401   0.03342  -0.0030   0.4619   1.0000
   7.250   0.6564   0.04287   0.03223  -0.0028   0.4581   1.0000
   7.750   0.6585   0.04526   0.03457   0.0023   0.4402   1.0000
   8.250   0.6645   0.04787   0.03717   0.0065   0.4223   1.0000
   8.500   0.7123   0.04605   0.03531   0.0065   0.4194   1.0000
   8.750   0.6706   0.05089   0.04019   0.0101   0.4043   1.0000
   9.000   0.7170   0.04895   0.03821   0.0104   0.4013   1.0000
   9.250   0.6780   0.05409   0.04339   0.0131   0.3862   1.0000
   9.500   0.7213   0.05225   0.04154   0.0137   0.3832   1.0000
   9.750   0.6825   0.05790   0.04723   0.0155   0.3681   1.0000
  10.000   0.7254   0.05587   0.04519   0.0164   0.3651   1.0000
  10.500   0.7269   0.06008   0.04945   0.0186   0.3472   1.0000
  11.000   0.7268   0.06480   0.05421   0.0202   0.3294   1.0000
  11.500   0.7240   0.07018   0.05964   0.0212   0.3120   1.0000
  12.000   0.7188   0.07623   0.06576   0.0217   0.2949   1.0000
  12.500   0.7099   0.08325   0.07285   0.0215   0.2782   1.0000
  13.000   0.6970   0.09141   0.08109   0.0205   0.2620   1.0000
  13.250   0.7289   0.08978   0.07948   0.0218   0.2600   1.0000
  13.750   0.7085   0.09952   0.08930   0.0199   0.2442   1.0000
  14.250   0.6852   0.11029   0.10014   0.0170   0.2292   1.0000
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