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RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAF-48 AIRFOIL (raf48-il)
Reynolds number: 200,000
Max Cl/Cd: 67.76 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf48-il-200000-n5.txt
Download as CSV file: xf-raf48-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.7708   0.06747   0.06280  -0.0688   1.0000   0.0306
 -14.500  -0.8027   0.05880   0.05391  -0.0751   1.0000   0.0305
 -14.250  -0.8228   0.05279   0.04769  -0.0792   1.0000   0.0308
 -14.000  -0.8386   0.04810   0.04280  -0.0817   1.0000   0.0311
 -13.750  -0.8513   0.04436   0.03887  -0.0829   1.0000   0.0315
 -13.500  -0.8613   0.04134   0.03565  -0.0829   1.0000   0.0319
 -13.250  -0.8705   0.03880   0.03288  -0.0820   1.0000   0.0324
 -13.000  -0.8757   0.03684   0.03077  -0.0804   1.0000   0.0330
 -12.750  -0.8745   0.03551   0.02942  -0.0784   1.0000   0.0335
 -12.500  -0.8737   0.03434   0.02821  -0.0760   1.0000   0.0339
 -12.250  -0.8735   0.03339   0.02722  -0.0730   1.0000   0.0346
 -12.000  -0.8752   0.03246   0.02622  -0.0693   1.0000   0.0352
 -11.750  -0.8775   0.03159   0.02525  -0.0653   1.0000   0.0358
 -11.500  -0.8774   0.03067   0.02423  -0.0615   1.0000   0.0365
 -11.250  -0.8572   0.02931   0.02264  -0.0617   0.9873   0.0377
 -11.000  -0.8308   0.02802   0.02126  -0.0629   0.9744   0.0388
 -10.750  -0.8013   0.02702   0.02022  -0.0645   0.9622   0.0401
 -10.500  -0.7707   0.02601   0.01907  -0.0661   0.9502   0.0415
 -10.250  -0.7389   0.02495   0.01783  -0.0678   0.9392   0.0431
 -10.000  -0.7071   0.02390   0.01661  -0.0694   0.9282   0.0446
  -9.750  -0.6769   0.02297   0.01564  -0.0707   0.9165   0.0461
  -9.500  -0.6472   0.02221   0.01478  -0.0717   0.9048   0.0477
  -9.250  -0.6192   0.02149   0.01392  -0.0722   0.8933   0.0496
  -9.000  -0.5948   0.02087   0.01313  -0.0719   0.8812   0.0511
  -8.750  -0.5732   0.02015   0.01238  -0.0711   0.8699   0.0527
  -8.500  -0.5506   0.01960   0.01176  -0.0704   0.8596   0.0545
  -8.250  -0.5296   0.01913   0.01120  -0.0693   0.8487   0.0566
  -8.000  -0.5074   0.01867   0.01060  -0.0683   0.8396   0.0588
  -7.750  -0.4870   0.01813   0.01004  -0.0671   0.8304   0.0610
  -7.500  -0.4655   0.01769   0.00954  -0.0660   0.8222   0.0635
  -7.250  -0.4435   0.01730   0.00907  -0.0649   0.8137   0.0666
  -7.000  -0.4214   0.01689   0.00860  -0.0639   0.8066   0.0703
  -6.750  -0.3991   0.01653   0.00822  -0.0629   0.7989   0.0749
  -6.500  -0.3760   0.01619   0.00780  -0.0620   0.7924   0.0800
  -6.250  -0.3534   0.01586   0.00746  -0.0610   0.7847   0.0865
  -6.000  -0.3303   0.01555   0.00712  -0.0600   0.7769   0.0941
  -5.750  -0.3069   0.01530   0.00681  -0.0591   0.7679   0.1032
  -5.500  -0.2835   0.01503   0.00651  -0.0582   0.7593   0.1131
  -5.250  -0.2600   0.01478   0.00625  -0.0573   0.7516   0.1232
  -5.000  -0.2358   0.01457   0.00600  -0.0566   0.7449   0.1336
  -4.750  -0.2111   0.01437   0.00576  -0.0559   0.7394   0.1452
  -4.500  -0.1873   0.01414   0.00557  -0.0551   0.7330   0.1567
  -4.250  -0.1630   0.01394   0.00536  -0.0543   0.7269   0.1692
  -4.000  -0.1383   0.01375   0.00515  -0.0537   0.7217   0.1830
  -3.750  -0.1142   0.01356   0.00500  -0.0529   0.7155   0.1984
  -3.500  -0.0901   0.01336   0.00485  -0.0521   0.7093   0.2166
  -3.250  -0.0657   0.01317   0.00468  -0.0514   0.7041   0.2397
  -3.000  -0.0421   0.01296   0.00457  -0.0506   0.6978   0.2660
  -2.750  -0.0184   0.01276   0.00445  -0.0497   0.6918   0.2937
  -2.500   0.0057   0.01256   0.00430  -0.0489   0.6866   0.3221
  -2.250   0.0286   0.01235   0.00421  -0.0479   0.6799   0.3545
  -2.000   0.0511   0.01211   0.00412  -0.0468   0.6735   0.3973
  -1.750   0.0734   0.01187   0.00403  -0.0456   0.6680   0.4510
  -1.500   0.0949   0.01163   0.00400  -0.0442   0.6612   0.5046
  -1.250   0.1165   0.01141   0.00396  -0.0428   0.6550   0.5603
  -1.000   0.1381   0.01119   0.00396  -0.0412   0.6489   0.6239
  -0.750   0.1610   0.01104   0.00401  -0.0399   0.6414   0.6822
  -0.500   0.1862   0.01095   0.00401  -0.0390   0.6350   0.7304
  -0.250   0.2125   0.01090   0.00408  -0.0383   0.6270   0.7715
   0.000   0.2411   0.01089   0.00410  -0.0381   0.6199   0.8060
   0.250   0.2714   0.01090   0.00414  -0.0383   0.6124   0.8355
   0.500   0.3042   0.01093   0.00417  -0.0391   0.6040   0.8637
   0.750   0.3460   0.01100   0.00424  -0.0417   0.5951   0.8862
   1.000   0.3874   0.01109   0.00429  -0.0444   0.5861   0.9016
   1.250   0.4275   0.01120   0.00437  -0.0468   0.5768   0.9142
   1.500   0.4732   0.01134   0.00443  -0.0503   0.5674   0.9245
   1.750   0.5149   0.01149   0.00457  -0.0530   0.5567   0.9366
   2.000   0.5512   0.01167   0.00468  -0.0546   0.5473   0.9483
   2.250   0.5837   0.01182   0.00479  -0.0556   0.5375   0.9588
   2.500   0.6191   0.01196   0.00488  -0.0572   0.5276   0.9654
   2.750   0.6510   0.01211   0.00496  -0.0581   0.5185   0.9733
   3.000   0.6857   0.01225   0.00508  -0.0597   0.5083   0.9806
   3.250   0.7232   0.01240   0.00517  -0.0618   0.4981   0.9876
   3.500   0.7604   0.01257   0.00527  -0.0640   0.4869   0.9942
   3.750   0.7972   0.01270   0.00536  -0.0661   0.4762   0.9992
   4.000   0.8188   0.01285   0.00545  -0.0651   0.4677   1.0000
   4.250   0.8372   0.01298   0.00558  -0.0634   0.4591   1.0000
   4.500   0.8553   0.01318   0.00571  -0.0617   0.4516   1.0000
   4.750   0.8745   0.01334   0.00589  -0.0602   0.4437   1.0000
   5.000   0.8933   0.01355   0.00606  -0.0585   0.4363   1.0000
   5.250   0.9127   0.01375   0.00626  -0.0570   0.4288   1.0000
   5.500   0.9317   0.01397   0.00647  -0.0554   0.4209   1.0000
   5.750   0.9511   0.01420   0.00670  -0.0539   0.4136   1.0000
   6.000   0.9705   0.01442   0.00694  -0.0524   0.4062   1.0000
   6.250   0.9895   0.01468   0.00719  -0.0508   0.3991   1.0000
   6.500   1.0087   0.01491   0.00746  -0.0492   0.3912   1.0000
   6.750   1.0269   0.01519   0.00772  -0.0475   0.3835   1.0000
   7.000   1.0456   0.01543   0.00801  -0.0459   0.3749   1.0000
   7.250   1.0630   0.01573   0.00831  -0.0440   0.3671   1.0000
   7.500   1.0810   0.01598   0.00863  -0.0423   0.3582   1.0000
   7.750   1.0973   0.01630   0.00895  -0.0403   0.3494   1.0000
   8.000   1.1130   0.01660   0.00929  -0.0382   0.3387   1.0000
   8.250   1.1269   0.01695   0.00965  -0.0358   0.3259   1.0000
   8.500   1.1383   0.01736   0.01004  -0.0331   0.3110   1.0000
   8.750   1.1462   0.01782   0.01046  -0.0297   0.2952   1.0000
   9.000   1.1506   0.01832   0.01091  -0.0258   0.2798   1.0000
   9.250   1.1543   0.01893   0.01147  -0.0220   0.2638   1.0000
   9.500   1.1593   0.01963   0.01211  -0.0187   0.2493   1.0000
   9.750   1.1642   0.02042   0.01286  -0.0157   0.2356   1.0000
  10.000   1.1688   0.02134   0.01373  -0.0128   0.2220   1.0000
  10.250   1.1737   0.02234   0.01469  -0.0103   0.2104   1.0000
  10.500   1.1812   0.02331   0.01567  -0.0082   0.1996   1.0000
  10.750   1.1888   0.02433   0.01671  -0.0063   0.1908   1.0000
  11.000   1.1951   0.02550   0.01788  -0.0044   0.1821   1.0000
  11.250   1.2036   0.02660   0.01901  -0.0029   0.1739   1.0000
  11.750   1.2170   0.02921   0.02166   0.0000   0.1577   1.0000
  12.000   1.2218   0.03072   0.02319   0.0014   0.1503   1.0000
  12.250   1.2285   0.03217   0.02468   0.0025   0.1419   1.0000
  12.500   1.2330   0.03382   0.02637   0.0036   0.1343   1.0000
  12.750   1.2366   0.03561   0.02817   0.0046   0.1257   1.0000
  13.000   1.2402   0.03745   0.03005   0.0055   0.1168   1.0000
  13.250   1.2413   0.03957   0.03218   0.0064   0.1082   1.0000
  13.500   1.2412   0.04185   0.03447   0.0071   0.0988   1.0000
  13.750   1.2409   0.04424   0.03687   0.0077   0.0884   1.0000
  14.000   1.2395   0.04684   0.03948   0.0082   0.0795   1.0000
  14.250   1.2366   0.04967   0.04230   0.0085   0.0719   1.0000
  14.500   1.2325   0.05273   0.04538   0.0087   0.0663   1.0000
  14.750   1.2300   0.05572   0.04841   0.0087   0.0616   1.0000
  15.000   1.2252   0.05907   0.05179   0.0086   0.0582   1.0000
  15.250   1.2234   0.06215   0.05496   0.0083   0.0553   1.0000
  15.500   1.2200   0.06551   0.05839   0.0080   0.0530   1.0000
  15.750   1.2145   0.06921   0.06214   0.0074   0.0507   1.0000
  16.000   1.2103   0.07280   0.06582   0.0068   0.0490   1.0000
  16.250   1.2080   0.07622   0.06934   0.0062   0.0472   1.0000
  16.500   1.2039   0.07995   0.07315   0.0054   0.0455   1.0000
  16.750   1.1984   0.08389   0.07716   0.0044   0.0442   1.0000
  17.000   1.1915   0.08810   0.08142   0.0033   0.0430   1.0000
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