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NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY RC-08(B)3 AIRFOIL (rc08b3-il)
Reynolds number: 500,000
Max Cl/Cd: 67.82 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rc08b3-il-500000.txt
Download as CSV file: xf-rc08b3-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY RC-08(B)3 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6041   0.10499   0.10271   0.0000   1.0000   0.0193
  -9.750  -0.6038   0.10005   0.09778  -0.0030   1.0000   0.0193
  -9.500  -0.6168   0.09333   0.09110  -0.0050   1.0000   0.0199
  -9.250  -0.6149   0.09001   0.08779  -0.0062   1.0000   0.0202
  -9.000  -0.6139   0.08624   0.08404  -0.0085   1.0000   0.0205
  -8.750  -0.6170   0.08138   0.07920  -0.0131   1.0000   0.0207
  -8.500  -0.6226   0.07657   0.07437  -0.0167   1.0000   0.0209
  -8.250  -0.6229   0.07213   0.06989  -0.0192   1.0000   0.0213
  -8.000  -0.6212   0.06757   0.06526  -0.0213   1.0000   0.0217
  -7.750  -0.6178   0.06294   0.06054  -0.0228   1.0000   0.0223
  -7.500  -0.6128   0.05824   0.05571  -0.0237   1.0000   0.0232
  -7.250  -0.5988   0.05295   0.05009  -0.0241   1.0000   0.0257
  -7.000  -0.5907   0.04918   0.04604  -0.0228   1.0000   0.0259
  -6.750  -0.5749   0.02835   0.02521  -0.0214   1.0000   0.0270
  -6.500  -0.5705   0.02648   0.02332  -0.0186   1.0000   0.0275
  -6.250  -0.5679   0.02489   0.02167  -0.0153   1.0000   0.0280
  -6.000  -0.5596   0.02310   0.01978  -0.0131   0.9994   0.0288
  -5.750  -0.5349   0.02017   0.01663  -0.0140   0.9967   0.0306
  -5.500  -0.4986   0.01990   0.01594  -0.0147   0.9943   0.0346
  -5.250  -0.4879   0.01339   0.00902  -0.0143   0.9903   0.0367
  -5.000  -0.4979   0.02176   0.01630  -0.0074   0.9934   0.0265
  -4.750  -0.4697   0.01807   0.01230  -0.0075   0.9907   0.0237
  -4.500  -0.4376   0.01615   0.01010  -0.0083   0.9882   0.0235
  -4.250  -0.4040   0.01474   0.00852  -0.0094   0.9862   0.0236
  -4.000  -0.3690   0.01380   0.00748  -0.0109   0.9844   0.0244
  -3.750  -0.3340   0.01297   0.00655  -0.0125   0.9827   0.0252
  -3.500  -0.3026   0.01218   0.00571  -0.0132   0.9787   0.0256
  -3.250  -0.2700   0.01129   0.00476  -0.0143   0.9755   0.0265
  -3.000  -0.2374   0.01050   0.00393  -0.0154   0.9724   0.0286
  -2.750  -0.2039   0.01008   0.00350  -0.0167   0.9692   0.0310
  -2.500  -0.1756   0.00981   0.00321  -0.0167   0.9625   0.0343
  -2.250  -0.1458   0.00936   0.00278  -0.0170   0.9574   0.0463
  -2.000  -0.1216   0.00875   0.00249  -0.0162   0.9498   0.1224
  -1.750  -0.0984   0.00809   0.00230  -0.0155   0.9426   0.2505
  -1.500  -0.0831   0.00696   0.00212  -0.0132   0.9330   0.5175
  -1.250  -0.0736   0.00569   0.00214  -0.0087   0.9248   0.8492
  -1.000  -0.0350   0.00593   0.00251  -0.0099   0.9190   0.9379
  -0.750   0.0024   0.00623   0.00275  -0.0111   0.9130   0.9609
  -0.500   0.0393   0.00638   0.00284  -0.0127   0.9047   0.9711
  -0.250   0.0883   0.00655   0.00294  -0.0170   0.8990   0.9807
   0.000   0.1543   0.00668   0.00304  -0.0250   0.8932   0.9951
   0.250   0.1987   0.00661   0.00291  -0.0286   0.8838   1.0000
   0.500   0.2235   0.00655   0.00280  -0.0280   0.8711   1.0000
   0.750   0.2486   0.00650   0.00271  -0.0274   0.8581   1.0000
   1.000   0.2736   0.00646   0.00262  -0.0267   0.8430   1.0000
   1.250   0.2988   0.00643   0.00254  -0.0261   0.8269   1.0000
   1.500   0.3245   0.00642   0.00248  -0.0256   0.8111   1.0000
   1.750   0.3502   0.00641   0.00243  -0.0252   0.7914   1.0000
   2.000   0.3758   0.00643   0.00238  -0.0246   0.7683   1.0000
   2.250   0.4014   0.00649   0.00234  -0.0241   0.7350   1.0000
   2.500   0.4269   0.00660   0.00230  -0.0236   0.6929   1.0000
   2.750   0.4526   0.00677   0.00230  -0.0231   0.6448   1.0000
   3.000   0.4781   0.00705   0.00234  -0.0227   0.5791   1.0000
   3.250   0.5031   0.00749   0.00243  -0.0224   0.4926   1.0000
   3.500   0.5278   0.00804   0.00259  -0.0222   0.3982   1.0000
   3.750   0.5523   0.00860   0.00278  -0.0219   0.3117   1.0000
   4.250   0.5999   0.00976   0.00328  -0.0212   0.1597   1.0000
   4.500   0.6226   0.01041   0.00361  -0.0206   0.0954   1.0000
   4.750   0.6454   0.01097   0.00399  -0.0198   0.0618   1.0000
   5.000   0.6684   0.01142   0.00442  -0.0190   0.0490   1.0000
   5.250   0.6904   0.01202   0.00501  -0.0180   0.0411   1.0000
   5.500   0.7134   0.01237   0.00541  -0.0171   0.0379   1.0000
   5.750   0.7356   0.01281   0.00586  -0.0161   0.0345   1.0000
   6.000   0.7546   0.01375   0.00685  -0.0146   0.0313   1.0000
   6.250   0.7765   0.01417   0.00735  -0.0135   0.0301   1.0000
   6.500   0.7975   0.01473   0.00797  -0.0122   0.0286   1.0000
   6.750   0.8184   0.01526   0.00855  -0.0110   0.0269   1.0000
   7.000   0.8387   0.01584   0.00914  -0.0098   0.0253   1.0000
   7.250   0.8536   0.01766   0.01107  -0.0076   0.0236   1.0000
   7.500   0.8742   0.01831   0.01182  -0.0063   0.0229   1.0000
   7.750   0.8946   0.01895   0.01256  -0.0050   0.0219   1.0000
   8.000   0.9146   0.01958   0.01327  -0.0037   0.0207   1.0000
   8.250   0.9341   0.02022   0.01399  -0.0024   0.0195   1.0000
   8.500   0.9527   0.02105   0.01488  -0.0009   0.0186   1.0000
   8.750   0.9669   0.02334   0.01732   0.0010   0.0176   1.0000
   9.000   0.9814   0.02529   0.01954   0.0030   0.0170   1.0000
   9.250   0.9980   0.02632   0.02078   0.0048   0.0163   1.0000
   9.500   1.0132   0.02753   0.02219   0.0067   0.0155   1.0000
   9.750   1.0281   0.02856   0.02336   0.0084   0.0147   1.0000
  10.000   1.0419   0.02971   0.02463   0.0102   0.0141   1.0000
  10.250   1.0541   0.03097   0.02604   0.0121   0.0137   1.0000
  10.500   1.0627   0.03286   0.02808   0.0142   0.0132   1.0000
  10.750   1.0574   0.03681   0.03238   0.0175   0.0129   1.0000
  11.000   1.0404   0.04166   0.03766   0.0215   0.0128   1.0000
  11.250   1.0212   0.04534   0.04163   0.0256   0.0127   1.0000
  11.500   1.0060   0.04826   0.04479   0.0283   0.0127   1.0000
  11.750   0.9869   0.05218   0.04894   0.0295   0.0126   1.0000
  12.000   0.9076   0.04219   0.03905   0.0359   0.0129   1.0000
  12.250   0.8862   0.04720   0.04423   0.0352   0.0130   1.0000
  12.500   0.8639   0.05316   0.05035   0.0332   0.0130   1.0000
  12.750   0.8388   0.06059   0.05795   0.0298   0.0131   1.0000
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