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RAF 27 AIRFOIL (raf27-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAF 27 AIRFOIL (raf27-il)
Reynolds number: 500,000
Max Cl/Cd: 56.77 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf27-il-500000.txt
Download as CSV file: xf-raf27-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 27 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.7423   0.10017   0.09777  -0.0079   1.0000   0.0151
 -12.750  -0.7784   0.08686   0.08445  -0.0154   1.0000   0.0145
 -12.500  -0.8324   0.06977   0.06719  -0.0280   1.0000   0.0133
 -12.250  -0.8474   0.06310   0.06039  -0.0335   1.0000   0.0136
 -12.000  -0.8994   0.05226   0.04922  -0.0401   1.0000   0.0128
 -11.750  -0.9595   0.04327   0.03970  -0.0404   1.0000   0.0123
 -11.500  -0.9486   0.04304   0.03950  -0.0394   1.0000   0.0127
 -11.250  -0.9644   0.04022   0.03646  -0.0362   1.0000   0.0128
 -11.000  -0.9707   0.03857   0.03468  -0.0326   1.0000   0.0131
 -10.750  -0.9772   0.03611   0.03197  -0.0290   1.0000   0.0133
 -10.500  -0.9748   0.03427   0.02992  -0.0263   1.0000   0.0138
 -10.250  -0.9731   0.03186   0.02722  -0.0232   1.0000   0.0141
 -10.000  -0.9677   0.02956   0.02464  -0.0204   1.0000   0.0143
  -9.750  -0.9581   0.02772   0.02253  -0.0180   1.0000   0.0147
  -9.500  -0.9451   0.02631   0.02090  -0.0158   1.0000   0.0150
  -9.250  -0.9351   0.02388   0.01818  -0.0134   1.0000   0.0155
  -9.000  -0.9219   0.02198   0.01613  -0.0113   1.0000   0.0160
  -8.750  -0.9047   0.02109   0.01519  -0.0097   1.0000   0.0166
  -8.500  -0.8865   0.02034   0.01438  -0.0082   1.0000   0.0174
  -8.250  -0.8677   0.01965   0.01361  -0.0067   1.0000   0.0183
  -8.000  -0.8481   0.01906   0.01293  -0.0052   1.0000   0.0194
  -7.750  -0.8280   0.01854   0.01230  -0.0038   1.0000   0.0201
  -7.500  -0.8152   0.01676   0.01041  -0.0013   1.0000   0.0214
  -7.250  -0.7972   0.01604   0.00968   0.0004   1.0000   0.0226
  -7.000  -0.7780   0.01549   0.00908   0.0020   1.0000   0.0241
  -6.750  -0.7578   0.01505   0.00859   0.0035   1.0000   0.0258
  -6.500  -0.7386   0.01452   0.00798   0.0051   1.0000   0.0273
  -6.250  -0.7236   0.01354   0.00697   0.0074   1.0000   0.0301
  -6.000  -0.7043   0.01308   0.00648   0.0091   1.0000   0.0326
  -5.750  -0.6843   0.01270   0.00605   0.0106   1.0000   0.0348
  -5.500  -0.6669   0.01206   0.00538   0.0126   1.0000   0.0388
  -5.250  -0.6474   0.01168   0.00498   0.0141   1.0000   0.0427
  -5.000  -0.6273   0.01138   0.00463   0.0156   1.0000   0.0462
  -4.750  -0.6085   0.01096   0.00426   0.0173   1.0000   0.0539
  -4.500  -0.5893   0.01060   0.00396   0.0189   1.0000   0.0678
  -4.250  -0.5614   0.01004   0.00359   0.0185   0.9983   0.1095
  -4.000  -0.5275   0.00929   0.00330   0.0166   0.9949   0.2023
  -3.750  -0.4935   0.00879   0.00309   0.0149   0.9910   0.2694
  -3.500  -0.4587   0.00837   0.00290   0.0130   0.9869   0.3286
  -3.250  -0.4222   0.00799   0.00275   0.0109   0.9837   0.3899
  -3.000  -0.3903   0.00763   0.00260   0.0099   0.9780   0.4488
  -2.750  -0.3553   0.00731   0.00247   0.0082   0.9734   0.5030
  -2.500  -0.3186   0.00698   0.00236   0.0062   0.9703   0.5597
  -2.250  -0.2889   0.00670   0.00225   0.0059   0.9626   0.6061
  -2.000  -0.2530   0.00644   0.00216   0.0043   0.9581   0.6559
  -1.750  -0.2194   0.00625   0.00207   0.0032   0.9512   0.6900
  -1.500  -0.1840   0.00606   0.00196   0.0018   0.9436   0.7183
  -1.250  -0.1511   0.00588   0.00187   0.0010   0.9320   0.7460
  -1.000  -0.1174   0.00575   0.00178   0.0000   0.9189   0.7680
  -0.750  -0.0852   0.00565   0.00171  -0.0006   0.9035   0.7877
  -0.500  -0.0552   0.00559   0.00166  -0.0008   0.8854   0.8077
  -0.250  -0.0271   0.00555   0.00163  -0.0005   0.8661   0.8268
   0.000   0.0000   0.00554   0.00163   0.0000   0.8463   0.8463
   0.250   0.0271   0.00555   0.00163   0.0005   0.8269   0.8663
   0.500   0.0551   0.00559   0.00166   0.0008   0.8077   0.8855
   0.750   0.0852   0.00565   0.00171   0.0006   0.7876   0.9035
   1.000   0.1174   0.00575   0.00178   0.0000   0.7680   0.9190
   1.250   0.1511   0.00588   0.00187  -0.0010   0.7463   0.9320
   1.500   0.1839   0.00606   0.00196  -0.0018   0.7188   0.9436
   1.750   0.2193   0.00625   0.00206  -0.0032   0.6887   0.9512
   2.000   0.2528   0.00645   0.00216  -0.0043   0.6534   0.9582
   2.250   0.2887   0.00670   0.00225  -0.0059   0.6048   0.9625
   2.500   0.3186   0.00697   0.00236  -0.0062   0.5602   0.9703
   2.750   0.3554   0.00730   0.00248  -0.0082   0.5044   0.9734
   3.000   0.3904   0.00762   0.00260  -0.0099   0.4509   0.9780
   3.250   0.4222   0.00798   0.00275  -0.0109   0.3910   0.9837
   3.500   0.4587   0.00837   0.00290  -0.0130   0.3290   0.9869
   3.750   0.4935   0.00880   0.00309  -0.0149   0.2684   0.9910
   4.000   0.5274   0.00929   0.00331  -0.0166   0.2019   0.9949
   4.250   0.5616   0.01002   0.00360  -0.0185   0.1113   0.9983
   4.500   0.5894   0.01061   0.00396  -0.0190   0.0674   1.0000
   4.750   0.6086   0.01096   0.00425  -0.0174   0.0538   1.0000
   5.000   0.6273   0.01140   0.00465  -0.0156   0.0458   1.0000
   5.250   0.6475   0.01168   0.00498  -0.0142   0.0426   1.0000
   5.500   0.6671   0.01206   0.00538  -0.0126   0.0388   1.0000
   5.750   0.6844   0.01270   0.00605  -0.0106   0.0349   1.0000
   6.000   0.7045   0.01308   0.00649  -0.0091   0.0326   1.0000
   6.250   0.7238   0.01353   0.00697  -0.0075   0.0301   1.0000
   6.500   0.7387   0.01452   0.00798  -0.0051   0.0274   1.0000
   6.750   0.7582   0.01502   0.00856  -0.0035   0.0257   1.0000
   7.000   0.7779   0.01551   0.00911  -0.0020   0.0241   1.0000
   7.250   0.7971   0.01607   0.00971  -0.0004   0.0227   1.0000
   7.500   0.8153   0.01676   0.01042   0.0013   0.0214   1.0000
   7.750   0.8278   0.01860   0.01235   0.0038   0.0201   1.0000
   8.000   0.8481   0.01908   0.01295   0.0052   0.0195   1.0000
   8.250   0.8676   0.01968   0.01364   0.0067   0.0184   1.0000
   8.500   0.8868   0.02026   0.01430   0.0081   0.0173   1.0000
   8.750   0.9050   0.02101   0.01511   0.0097   0.0166   1.0000
   9.000   0.9218   0.02204   0.01620   0.0113   0.0161   1.0000
   9.250   0.9340   0.02412   0.01843   0.0135   0.0153   1.0000
   9.500   0.9452   0.02626   0.02085   0.0158   0.0149   1.0000
   9.750   0.9585   0.02759   0.02241   0.0180   0.0146   1.0000
  10.000   0.9681   0.02947   0.02454   0.0204   0.0143   1.0000
  10.250   0.9736   0.03171   0.02707   0.0232   0.0139   1.0000
  10.500   0.9774   0.03381   0.02943   0.0260   0.0136   1.0000
  10.750   0.9765   0.03620   0.03207   0.0291   0.0133   1.0000
  11.000   0.9828   0.03719   0.03316   0.0314   0.0127   1.0000
  11.250   0.9640   0.04025   0.03650   0.0363   0.0128   1.0000
  11.500   0.9697   0.04085   0.03712   0.0382   0.0124   1.0000
  11.750   0.9587   0.04336   0.03978   0.0404   0.0122   1.0000
  12.000   0.9269   0.04873   0.04549   0.0411   0.0124   1.0000
  12.250   0.8574   0.06144   0.05869   0.0345   0.0130   1.0000
  12.500   0.8125   0.07423   0.07171   0.0245   0.0139   1.0000
  12.750   0.7762   0.08778   0.08538   0.0146   0.0145   1.0000
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