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RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RAF 30 AIRFOIL (raf30-il)
Reynolds number: 50,000
Max Cl/Cd: 28.37 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf30-il-50000.txt
Download as CSV file: xf-raf30-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 30 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6085   0.11591   0.10812  -0.0086   1.0000   0.2066
 -11.000  -0.6171   0.10468   0.09690  -0.0140   1.0000   0.1732
 -10.750  -0.7480   0.08047   0.07292  -0.0337   1.0000   0.1465
 -10.500  -0.7659   0.07498   0.06741  -0.0345   1.0000   0.1451
 -10.250  -0.7911   0.07004   0.06243  -0.0340   1.0000   0.1434
 -10.000  -0.8199   0.06553   0.05779  -0.0318   1.0000   0.1418
  -9.750  -0.8437   0.06107   0.05310  -0.0294   1.0000   0.1406
  -9.500  -0.8579   0.05705   0.04879  -0.0269   1.0000   0.1403
  -9.250  -0.8657   0.05327   0.04468  -0.0243   1.0000   0.1406
  -9.000  -0.8679   0.04973   0.04077  -0.0216   1.0000   0.1413
  -8.750  -0.8657   0.04645   0.03707  -0.0190   1.0000   0.1427
  -8.500  -0.8618   0.04358   0.03370  -0.0162   1.0000   0.1456
  -8.250  -0.8475   0.04090   0.03088  -0.0146   1.0000   0.1506
  -8.000  -0.8307   0.03865   0.02848  -0.0130   1.0000   0.1568
  -7.750  -0.8161   0.03620   0.02560  -0.0109   1.0000   0.1626
  -7.500  -0.7944   0.03418   0.02364  -0.0098   1.0000   0.1732
  -7.250  -0.7746   0.03227   0.02173  -0.0084   1.0000   0.1876
  -7.000  -0.7549   0.03031   0.01979  -0.0067   1.0000   0.2078
  -6.750  -0.7390   0.02861   0.01842  -0.0045   1.0000   0.2402
  -6.500  -0.7287   0.02710   0.01727  -0.0013   1.0000   0.2862
  -6.250  -0.7195   0.02589   0.01647   0.0023   1.0000   0.3384
  -6.000  -0.7113   0.02507   0.01597   0.0063   1.0000   0.3930
  -5.750  -0.7015   0.02494   0.01628   0.0106   1.0000   0.4477
  -5.500  -0.6896   0.02517   0.01678   0.0151   1.0000   0.5000
  -5.250  -0.6729   0.02544   0.01722   0.0191   1.0000   0.5443
  -5.000  -0.6568   0.02550   0.01730   0.0228   1.0000   0.5824
  -4.750  -0.6404   0.02557   0.01737   0.0263   1.0000   0.6166
  -4.500  -0.6203   0.02582   0.01763   0.0296   1.0000   0.6475
  -4.250  -0.5982   0.02618   0.01796   0.0327   1.0000   0.6766
  -4.000  -0.5763   0.02651   0.01824   0.0358   1.0000   0.7053
  -3.750  -0.5550   0.02680   0.01847   0.0389   1.0000   0.7344
  -3.500  -0.5334   0.02705   0.01865   0.0417   1.0000   0.7640
  -3.250  -0.4948   0.02768   0.01914   0.0422   1.0000   0.7926
  -3.000  -0.4415   0.02828   0.01955   0.0397   1.0000   0.8188
  -2.750  -0.4114   0.02818   0.01931   0.0395   1.0000   0.8447
  -2.500  -0.3229   0.02859   0.01945   0.0299   1.0000   0.8663
  -2.250  -0.2630   0.02843   0.01911   0.0240   1.0000   0.8884
  -2.000  -0.2170   0.02811   0.01868   0.0199   1.0000   0.9103
  -1.750  -0.1518   0.02768   0.01812   0.0122   1.0000   0.9305
  -1.500  -0.0972   0.02717   0.01753   0.0059   1.0000   0.9511
  -1.250  -0.0417   0.02658   0.01689  -0.0011   1.0000   0.9715
  -1.000   0.0239   0.02575   0.01601  -0.0102   1.0000   0.9914
  -0.750   0.0483   0.02537   0.01564  -0.0126   1.0000   1.0000
  -0.500   0.0328   0.02551   0.01581  -0.0084   1.0000   1.0000
  -0.250   0.0164   0.02561   0.01592  -0.0042   1.0000   1.0000
   0.000   0.0000   0.02565   0.01597   0.0000   1.0000   1.0000
   0.250  -0.0165   0.02561   0.01592   0.0042   1.0000   1.0000
   0.500  -0.0328   0.02551   0.01581   0.0084   1.0000   1.0000
   0.750  -0.0484   0.02537   0.01564   0.0126   1.0000   1.0000
   1.000  -0.0232   0.02575   0.01602   0.0101   0.9912   1.0000
   1.250   0.0420   0.02658   0.01688   0.0010   0.9714   1.0000
   1.500   0.0972   0.02716   0.01752  -0.0059   0.9511   1.0000
   1.750   0.1519   0.02767   0.01811  -0.0122   0.9304   1.0000
   2.000   0.2164   0.02811   0.01867  -0.0198   0.9104   1.0000
   2.250   0.2630   0.02842   0.01910  -0.0240   0.8884   1.0000
   2.500   0.3231   0.02858   0.01944  -0.0299   0.8663   1.0000
   2.750   0.4101   0.02819   0.01933  -0.0394   0.8448   1.0000
   3.000   0.4414   0.02827   0.01955  -0.0397   0.8188   1.0000
   3.250   0.4948   0.02768   0.01914  -0.0422   0.7926   1.0000
   3.500   0.5337   0.02703   0.01863  -0.0417   0.7639   1.0000
   3.750   0.5549   0.02679   0.01846  -0.0389   0.7344   1.0000
   4.000   0.5762   0.02651   0.01824  -0.0358   0.7054   1.0000
   4.250   0.5982   0.02618   0.01796  -0.0328   0.6767   1.0000
   4.500   0.6203   0.02582   0.01763  -0.0296   0.6476   1.0000
   4.750   0.6405   0.02557   0.01737  -0.0264   0.6168   1.0000
   5.000   0.6568   0.02550   0.01729  -0.0228   0.5825   1.0000
   5.250   0.6729   0.02544   0.01723  -0.0191   0.5443   1.0000
   5.500   0.6896   0.02517   0.01679  -0.0151   0.5001   1.0000
   5.750   0.7015   0.02494   0.01627  -0.0106   0.4476   1.0000
   6.000   0.7113   0.02507   0.01597  -0.0063   0.3930   1.0000
   6.250   0.7194   0.02589   0.01646  -0.0023   0.3381   1.0000
   6.500   0.7287   0.02710   0.01726   0.0013   0.2860   1.0000
   6.750   0.7390   0.02861   0.01843   0.0045   0.2403   1.0000
   7.000   0.7550   0.03032   0.01980   0.0067   0.2078   1.0000
   7.250   0.7746   0.03227   0.02173   0.0084   0.1875   1.0000
   7.500   0.7943   0.03418   0.02364   0.0099   0.1731   1.0000
   7.750   0.8161   0.03619   0.02559   0.0109   0.1626   1.0000
   8.000   0.8307   0.03865   0.02847   0.0130   0.1568   1.0000
   8.250   0.8475   0.04093   0.03092   0.0146   0.1507   1.0000
   8.500   0.8618   0.04358   0.03370   0.0162   0.1456   1.0000
   8.750   0.8656   0.04647   0.03710   0.0190   0.1427   1.0000
   9.000   0.8679   0.04974   0.04078   0.0216   0.1413   1.0000
   9.250   0.8658   0.05328   0.04469   0.0242   0.1406   1.0000
   9.500   0.8580   0.05706   0.04880   0.0269   0.1403   1.0000
   9.750   0.8436   0.06112   0.05315   0.0294   0.1406   1.0000
  10.000   0.8203   0.06554   0.05780   0.0318   0.1418   1.0000
  10.250   0.7925   0.07006   0.06245   0.0338   0.1436   1.0000
  10.500   0.7663   0.07502   0.06745   0.0345   0.1451   1.0000
  10.750   0.7497   0.08047   0.07293   0.0337   0.1465   1.0000
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