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RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAF-48 AIRFOIL (raf48-il)
Reynolds number: 100,000
Max Cl/Cd: 49.19 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf48-il-100000-n5.txt
Download as CSV file: xf-raf48-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF-48 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6096   0.06797   0.06229  -0.0699   1.0000   0.0501
 -12.250  -0.6625   0.05813   0.05223  -0.0768   1.0000   0.0495
 -12.000  -0.6977   0.05282   0.04670  -0.0781   1.0000   0.0495
 -11.750  -0.7255   0.04930   0.04297  -0.0765   1.0000   0.0498
 -11.500  -0.7508   0.04676   0.04024  -0.0726   1.0000   0.0502
 -11.250  -0.7727   0.04466   0.03793  -0.0676   1.0000   0.0506
 -11.000  -0.7922   0.04257   0.03555  -0.0626   1.0000   0.0512
 -10.750  -0.7936   0.04140   0.03441  -0.0592   1.0000   0.0519
 -10.500  -0.7987   0.04053   0.03354  -0.0550   0.9998   0.0526
 -10.250  -0.7734   0.03870   0.03157  -0.0568   0.9883   0.0542
 -10.000  -0.7502   0.03673   0.02932  -0.0581   0.9766   0.0561
  -9.750  -0.7274   0.03459   0.02677  -0.0591   0.9656   0.0584
  -9.500  -0.6991   0.03279   0.02475  -0.0607   0.9574   0.0603
  -9.250  -0.6707   0.03155   0.02345  -0.0618   0.9480   0.0622
  -9.000  -0.6395   0.03024   0.02196  -0.0634   0.9411   0.0648
  -8.750  -0.6123   0.02890   0.02031  -0.0640   0.9314   0.0676
  -8.500  -0.5807   0.02766   0.01900  -0.0655   0.9245   0.0701
  -8.250  -0.5532   0.02673   0.01802  -0.0660   0.9151   0.0726
  -8.000  -0.5225   0.02577   0.01687  -0.0669   0.9082   0.0765
  -7.750  -0.4971   0.02492   0.01592  -0.0669   0.8985   0.0800
  -7.500  -0.4692   0.02418   0.01514  -0.0672   0.8911   0.0838
  -7.250  -0.4449   0.02351   0.01432  -0.0667   0.8817   0.0884
  -7.000  -0.4191   0.02285   0.01364  -0.0666   0.8743   0.0936
  -6.750  -0.3958   0.02233   0.01304  -0.0659   0.8652   0.1001
  -6.500  -0.3706   0.02175   0.01243  -0.0656   0.8582   0.1070
  -6.250  -0.3480   0.02133   0.01190  -0.0647   0.8494   0.1158
  -6.000  -0.3227   0.02082   0.01141  -0.0643   0.8432   0.1253
  -5.750  -0.3020   0.02045   0.01103  -0.0631   0.8342   0.1356
  -5.500  -0.2767   0.02006   0.01057  -0.0626   0.8275   0.1481
  -5.250  -0.2550   0.01974   0.01023  -0.0614   0.8188   0.1610
  -5.000  -0.2309   0.01935   0.00984  -0.0606   0.8108   0.1744
  -4.750  -0.2093   0.01905   0.00954  -0.0594   0.8015   0.1885
  -4.500  -0.1851   0.01871   0.00919  -0.0586   0.7938   0.2045
  -4.250  -0.1629   0.01843   0.00895  -0.0575   0.7855   0.2224
  -4.000  -0.1393   0.01815   0.00868  -0.0566   0.7783   0.2435
  -3.750  -0.1156   0.01785   0.00843  -0.0557   0.7720   0.2669
  -3.500  -0.0939   0.01759   0.00825  -0.0545   0.7642   0.2924
  -3.250  -0.0696   0.01726   0.00797  -0.0537   0.7582   0.3216
  -3.000  -0.0482   0.01700   0.00784  -0.0524   0.7508   0.3553
  -2.750  -0.0262   0.01669   0.00769  -0.0512   0.7439   0.3984
  -2.500  -0.0026   0.01636   0.00752  -0.0501   0.7382   0.4530
  -2.250   0.0175   0.01613   0.00752  -0.0485   0.7302   0.5118
  -2.000   0.0418   0.01583   0.00746  -0.0474   0.7239   0.5799
  -1.750   0.0670   0.01567   0.00752  -0.0463   0.7170   0.6513
  -1.500   0.0949   0.01561   0.00760  -0.0457   0.7097   0.7118
  -1.250   0.1278   0.01556   0.00758  -0.0460   0.7041   0.7626
  -1.000   0.1579   0.01565   0.00772  -0.0459   0.6955   0.8026
  -0.750   0.1930   0.01569   0.00771  -0.0467   0.6887   0.8364
  -0.500   0.2286   0.01580   0.00779  -0.0478   0.6810   0.8659
  -0.250   0.2726   0.01592   0.00785  -0.0505   0.6733   0.8889
   0.000   0.3164   0.01603   0.00788  -0.0532   0.6660   0.9067
   0.250   0.3589   0.01616   0.00794  -0.0559   0.6569   0.9206
   0.500   0.3999   0.01625   0.00794  -0.0582   0.6495   0.9333
   0.750   0.4428   0.01642   0.00807  -0.0610   0.6401   0.9485
   1.000   0.4882   0.01651   0.00807  -0.0644   0.6324   0.9638
   1.250   0.5286   0.01659   0.00811  -0.0670   0.6224   0.9760
   1.500   0.5664   0.01661   0.00806  -0.0692   0.6140   0.9850
   1.750   0.6044   0.01664   0.00806  -0.0716   0.6047   0.9933
   2.000   0.6419   0.01663   0.00801  -0.0738   0.5958   1.0000
   2.250   0.6599   0.01668   0.00802  -0.0722   0.5873   1.0000
   2.500   0.6779   0.01677   0.00808  -0.0706   0.5791   1.0000
   2.750   0.6961   0.01686   0.00814  -0.0689   0.5708   1.0000
   3.000   0.7144   0.01698   0.00823  -0.0673   0.5628   1.0000
   3.250   0.7328   0.01712   0.00834  -0.0656   0.5545   1.0000
   3.500   0.7517   0.01727   0.00846  -0.0640   0.5468   1.0000
   3.750   0.7704   0.01743   0.00860  -0.0624   0.5383   1.0000
   4.000   0.7896   0.01760   0.00875  -0.0608   0.5301   1.0000
   4.250   0.8087   0.01778   0.00890  -0.0592   0.5211   1.0000
   4.500   0.8276   0.01799   0.00909  -0.0576   0.5123   1.0000
   4.750   0.8475   0.01817   0.00924  -0.0561   0.5038   1.0000
   5.000   0.8662   0.01842   0.00950  -0.0545   0.4948   1.0000
   5.250   0.8865   0.01862   0.00966  -0.0531   0.4866   1.0000
   5.500   0.9049   0.01892   0.00998  -0.0514   0.4777   1.0000
   5.750   0.9254   0.01914   0.01016  -0.0500   0.4695   1.0000
   6.000   0.9431   0.01947   0.01054  -0.0483   0.4605   1.0000
   6.250   0.9637   0.01972   0.01074  -0.0469   0.4525   1.0000
   6.500   0.9805   0.02008   0.01118  -0.0451   0.4431   1.0000
   6.750   1.0011   0.02035   0.01140  -0.0437   0.4350   1.0000
   7.000   1.0164   0.02074   0.01188  -0.0417   0.4253   1.0000
   7.250   1.0359   0.02106   0.01217  -0.0402   0.4170   1.0000
   7.500   1.0507   0.02147   0.01268  -0.0381   0.4072   1.0000
   7.750   1.0680   0.02183   0.01305  -0.0363   0.3984   1.0000
   8.000   1.0822   0.02225   0.01354  -0.0341   0.3885   1.0000
   8.250   1.0966   0.02268   0.01403  -0.0319   0.3788   1.0000
   8.500   1.1105   0.02309   0.01446  -0.0297   0.3689   1.0000
   8.750   1.1212   0.02359   0.01506  -0.0270   0.3582   1.0000
   9.000   1.1330   0.02407   0.01557  -0.0245   0.3482   1.0000
   9.250   1.1405   0.02458   0.01613  -0.0213   0.3375   1.0000
   9.500   1.1461   0.02516   0.01679  -0.0180   0.3265   1.0000
   9.750   1.1520   0.02579   0.01743  -0.0149   0.3153   1.0000
  10.000   1.1569   0.02650   0.01813  -0.0119   0.3034   1.0000
  10.250   1.1603   0.02739   0.01904  -0.0090   0.2903   1.0000
  10.500   1.1628   0.02841   0.02006  -0.0062   0.2766   1.0000
  10.750   1.1640   0.02960   0.02123  -0.0037   0.2623   1.0000
  11.000   1.1646   0.03097   0.02256  -0.0014   0.2482   1.0000
  11.250   1.1654   0.03245   0.02401   0.0007   0.2352   1.0000
  11.500   1.1670   0.03402   0.02555   0.0025   0.2241   1.0000
  11.750   1.1694   0.03564   0.02719   0.0040   0.2140   1.0000
  12.000   1.1725   0.03730   0.02890   0.0053   0.2050   1.0000
  12.250   1.1739   0.03912   0.03072   0.0066   0.1964   1.0000
  12.500   1.1769   0.04096   0.03266   0.0077   0.1880   1.0000
  12.750   1.1772   0.04301   0.03470   0.0087   0.1801   1.0000
  13.000   1.1783   0.04514   0.03694   0.0095   0.1715   1.0000
  13.250   1.1776   0.04744   0.03926   0.0102   0.1639   1.0000
  13.500   1.1768   0.04988   0.04179   0.0107   0.1558   1.0000
  13.750   1.1748   0.05251   0.04447   0.0111   0.1481   1.0000
  14.000   1.1719   0.05534   0.04738   0.0113   0.1402   1.0000
  14.250   1.1687   0.05834   0.05045   0.0114   0.1323   1.0000
  14.500   1.1628   0.06171   0.05384   0.0112   0.1246   1.0000
  14.750   1.1584   0.06511   0.05734   0.0109   0.1163   1.0000
  15.000   1.1518   0.06881   0.06105   0.0104   0.1094   1.0000
  15.250   1.1467   0.07250   0.06483   0.0098   0.1021   1.0000
  15.500   1.1400   0.07644   0.06879   0.0090   0.0958   1.0000
  15.750   1.1336   0.08045   0.07287   0.0081   0.0896   1.0000
  16.000   1.1272   0.08451   0.07695   0.0071   0.0846   1.0000
  16.250   1.1217   0.08855   0.08106   0.0061   0.0798   1.0000
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