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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 100,000
Max Cl/Cd: 45.73 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg14a147-il-100000-n5.txt
Download as CSV file: xf-rg14a147-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14A-1.4/7.0 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4368   0.08942   0.08471  -0.0149   1.0000   0.0234
  -8.750  -0.4370   0.08516   0.08048  -0.0159   1.0000   0.0226
  -8.500  -0.5186   0.09006   0.08515  -0.0149   1.0000   0.0235
  -8.250  -0.5186   0.08620   0.08134  -0.0163   1.0000   0.0226
  -8.000  -0.5207   0.08222   0.07743  -0.0183   1.0000   0.0219
  -7.750  -0.5253   0.07798   0.07325  -0.0209   1.0000   0.0212
  -7.500  -0.5262   0.07315   0.06844  -0.0243   1.0000   0.0204
  -7.250  -0.5252   0.06823   0.06349  -0.0273   1.0000   0.0197
  -7.000  -0.5230   0.06292   0.05811  -0.0298   1.0000   0.0189
  -6.750  -0.5191   0.05713   0.05217  -0.0318   1.0000   0.0178
  -6.500  -0.5125   0.05060   0.04530  -0.0329   1.0000   0.0166
  -6.250  -0.4998   0.04651   0.04088  -0.0326   1.0000   0.0159
  -5.750  -0.4741   0.03938   0.03307  -0.0310   1.0000   0.0155
  -5.500  -0.4597   0.03576   0.02895  -0.0301   1.0000   0.0154
  -5.000  -0.4270   0.02908   0.02143  -0.0281   1.0000   0.0172
  -4.750  -0.4072   0.02741   0.01954  -0.0272   1.0000   0.0196
  -4.500  -0.3854   0.02513   0.01684  -0.0260   1.0000   0.0207
  -4.250  -0.3626   0.02290   0.01420  -0.0247   1.0000   0.0213
  -4.000  -0.3393   0.02100   0.01199  -0.0233   1.0000   0.0224
  -3.750  -0.3162   0.01941   0.01018  -0.0220   1.0000   0.0239
  -3.500  -0.2942   0.01798   0.00863  -0.0208   1.0000   0.0265
  -3.250  -0.2722   0.01710   0.00772  -0.0198   1.0000   0.0347
  -3.000  -0.2500   0.01602   0.00652  -0.0186   1.0000   0.0407
  -2.750  -0.2275   0.01509   0.00558  -0.0175   1.0000   0.0601
  -2.500  -0.2059   0.01397   0.00490  -0.0167   1.0000   0.1530
  -2.250  -0.1868   0.01244   0.00463  -0.0159   1.0000   0.4229
  -2.000  -0.1734   0.01139   0.00470  -0.0122   1.0000   0.6991
  -1.750  -0.1528   0.01121   0.00483  -0.0090   1.0000   0.8904
  -1.500  -0.0780   0.01116   0.00449  -0.0179   1.0000   1.0000
  -1.250  -0.0636   0.01117   0.00434  -0.0159   1.0000   1.0000
  -1.000  -0.0446   0.01122   0.00418  -0.0147   0.9991   1.0000
  -0.750  -0.0024   0.01132   0.00410  -0.0181   0.9896   1.0000
  -0.500   0.0394   0.01142   0.00405  -0.0213   0.9799   1.0000
  -0.250   0.0805   0.01147   0.00400  -0.0243   0.9693   1.0000
   0.000   0.1197   0.01148   0.00390  -0.0268   0.9572   1.0000
   0.250   0.1591   0.01147   0.00384  -0.0293   0.9448   1.0000
   0.500   0.1981   0.01144   0.00378  -0.0316   0.9316   1.0000
   0.750   0.2360   0.01140   0.00374  -0.0336   0.9169   1.0000
   1.000   0.2723   0.01137   0.00370  -0.0351   0.8998   1.0000
   1.250   0.3067   0.01133   0.00367  -0.0363   0.8798   1.0000
   1.500   0.3411   0.01131   0.00365  -0.0373   0.8584   1.0000
   1.750   0.3738   0.01130   0.00367  -0.0379   0.8345   1.0000
   2.000   0.4033   0.01133   0.00369  -0.0378   0.8068   1.0000
   2.250   0.4313   0.01140   0.00374  -0.0374   0.7761   1.0000
   2.500   0.4589   0.01151   0.00380  -0.0368   0.7449   1.0000
   2.750   0.4844   0.01167   0.00400  -0.0360   0.7110   1.0000
   3.000   0.5087   0.01186   0.00415  -0.0349   0.6720   1.0000
   3.250   0.5327   0.01210   0.00431  -0.0338   0.6310   1.0000
   3.500   0.5560   0.01239   0.00451  -0.0325   0.5863   1.0000
   3.750   0.5788   0.01275   0.00474  -0.0313   0.5389   1.0000
   4.000   0.6013   0.01315   0.00503  -0.0300   0.4881   1.0000
   4.250   0.6232   0.01363   0.00545  -0.0288   0.4336   1.0000
   4.500   0.6447   0.01419   0.00584  -0.0276   0.3746   1.0000
   4.750   0.6656   0.01486   0.00630  -0.0264   0.3086   1.0000
   5.000   0.6855   0.01573   0.00684  -0.0253   0.2301   1.0000
   5.250   0.7045   0.01687   0.00749  -0.0242   0.1429   1.0000
   5.500   0.7248   0.01798   0.00837  -0.0232   0.0904   1.0000
   5.750   0.7442   0.01931   0.00947  -0.0221   0.0575   1.0000
   6.000   0.7646   0.02047   0.01067  -0.0209   0.0428   1.0000
   6.250   0.7848   0.02168   0.01202  -0.0197   0.0365   1.0000
   6.500   0.8032   0.02325   0.01384  -0.0182   0.0332   1.0000
   6.750   0.8235   0.02484   0.01566  -0.0168   0.0309   1.0000
   7.000   0.8445   0.02673   0.01778  -0.0155   0.0286   1.0000
   7.250   0.8639   0.02828   0.01943  -0.0146   0.0242   1.0000
   7.500   0.8830   0.03103   0.02249  -0.0134   0.0218   1.0000
   7.750   0.9019   0.03391   0.02583  -0.0119   0.0204   1.0000
   8.000   0.9177   0.03683   0.02924  -0.0103   0.0185   1.0000
   8.250   0.9317   0.03877   0.03148  -0.0091   0.0159   1.0000
   8.500   0.9413   0.04146   0.03441  -0.0079   0.0145   1.0000
   9.000   0.9410   0.05013   0.04395  -0.0042   0.0137   1.0000
   9.250   0.9360   0.05403   0.04826  -0.0024   0.0136   1.0000
   9.500   0.9263   0.05785   0.05239  -0.0008   0.0135   1.0000
   9.750   0.9108   0.06152   0.05629   0.0008   0.0135   1.0000
  10.000   0.8939   0.06565   0.06060   0.0006   0.0135   1.0000
  10.250   0.8771   0.07059   0.06568  -0.0016   0.0137   1.0000
  10.500   0.8600   0.07675   0.07196  -0.0059   0.0137   1.0000
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