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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 1,000,000
Max Cl/Cd: 76.53 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg14a147-il-1000000-n5.txt
Download as CSV file: xf-rg14a147-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5383   0.08361   0.08202  -0.0137   1.0000   0.0027
  -8.500  -0.5420   0.07916   0.07760  -0.0161   1.0000   0.0026
  -8.250  -0.5488   0.07476   0.07323  -0.0187   1.0000   0.0026
  -8.000  -0.5590   0.06961   0.06810  -0.0232   1.0000   0.0024
  -7.750  -0.5604   0.06404   0.06250  -0.0274   1.0000   0.0026
  -7.500  -0.5605   0.05828   0.05667  -0.0303   1.0000   0.0026
  -7.250  -0.5590   0.05256   0.05084  -0.0320   1.0000   0.0026
  -7.000  -0.5558   0.04681   0.04494  -0.0325   1.0000   0.0027
  -6.750  -0.5510   0.04114   0.03907  -0.0320   1.0000   0.0027
  -6.500  -0.5418   0.03450   0.03212  -0.0316   0.9995   0.0027
  -6.250  -0.5171   0.02807   0.02530  -0.0332   0.9970   0.0029
  -6.000  -0.4902   0.02300   0.01978  -0.0344   0.9946   0.0031
  -5.750  -0.4644   0.01900   0.01530  -0.0347   0.9917   0.0031
  -5.500  -0.4371   0.01591   0.01176  -0.0350   0.9885   0.0031
  -5.250  -0.4076   0.01374   0.00924  -0.0355   0.9857   0.0030
  -5.000  -0.3767   0.01209   0.00731  -0.0362   0.9835   0.0030
  -4.750  -0.3455   0.01077   0.00578  -0.0370   0.9813   0.0031
  -4.500  -0.3189   0.00989   0.00477  -0.0367   0.9756   0.0031
  -4.250  -0.2884   0.00913   0.00389  -0.0373   0.9711   0.0033
  -4.000  -0.2583   0.00859   0.00325  -0.0378   0.9653   0.0035
  -3.750  -0.2275   0.00801   0.00255  -0.0384   0.9579   0.0044
  -3.500  -0.1960   0.00767   0.00218  -0.0391   0.9487   0.0062
  -3.250  -0.1643   0.00744   0.00191  -0.0400   0.9366   0.0081
  -3.000  -0.1345   0.00722   0.00163  -0.0403   0.9200   0.0126
  -2.750  -0.1067   0.00706   0.00142  -0.0402   0.9000   0.0203
  -2.500  -0.0805   0.00686   0.00124  -0.0398   0.8777   0.0457
  -2.250  -0.0545   0.00672   0.00110  -0.0394   0.8544   0.0700
  -2.000  -0.0286   0.00659   0.00098  -0.0390   0.8304   0.1022
  -1.750  -0.0033   0.00639   0.00087  -0.0385   0.8029   0.1611
  -1.500   0.0214   0.00610   0.00076  -0.0380   0.7739   0.2543
  -1.250   0.0473   0.00600   0.00069  -0.0377   0.7526   0.3032
  -1.000   0.0735   0.00586   0.00064  -0.0374   0.7358   0.3592
  -0.750   0.0994   0.00561   0.00061  -0.0372   0.7189   0.4458
  -0.500   0.1252   0.00538   0.00056  -0.0369   0.6966   0.5324
  -0.250   0.1485   0.00495   0.00054  -0.0361   0.6652   0.6925
   0.000   0.1725   0.00483   0.00059  -0.0352   0.6352   0.7830
   0.250   0.1982   0.00489   0.00062  -0.0347   0.6065   0.8132
   0.500   0.2241   0.00497   0.00065  -0.0342   0.5780   0.8374
   0.750   0.2500   0.00506   0.00069  -0.0338   0.5497   0.8561
   1.000   0.2760   0.00516   0.00073  -0.0333   0.5205   0.8723
   1.250   0.3015   0.00528   0.00079  -0.0328   0.4890   0.8886
   1.500   0.3269   0.00542   0.00085  -0.0322   0.4571   0.9030
   1.750   0.3518   0.00557   0.00093  -0.0316   0.4237   0.9185
   2.000   0.3764   0.00571   0.00100  -0.0308   0.3928   0.9362
   2.250   0.4020   0.00587   0.00109  -0.0303   0.3610   0.9558
   2.500   0.4321   0.00609   0.00119  -0.0308   0.3241   0.9721
   2.750   0.4635   0.00639   0.00131  -0.0318   0.2756   0.9831
   3.000   0.4950   0.00674   0.00147  -0.0329   0.2256   0.9898
   3.250   0.5250   0.00718   0.00166  -0.0337   0.1652   0.9960
   3.500   0.5531   0.00759   0.00186  -0.0341   0.1175   1.0000
   3.750   0.5774   0.00788   0.00204  -0.0335   0.0929   1.0000
   4.000   0.6020   0.00819   0.00224  -0.0330   0.0685   1.0000
   4.250   0.6268   0.00850   0.00249  -0.0325   0.0486   1.0000
   4.500   0.6518   0.00881   0.00274  -0.0320   0.0320   1.0000
   4.750   0.6769   0.00914   0.00301  -0.0316   0.0194   1.0000
   5.000   0.7024   0.00944   0.00329  -0.0312   0.0138   1.0000
   5.250   0.7283   0.00968   0.00357  -0.0309   0.0127   1.0000
   5.500   0.7539   0.00997   0.00389  -0.0305   0.0114   1.0000
   5.750   0.7793   0.01029   0.00421  -0.0301   0.0095   1.0000
   6.000   0.8043   0.01068   0.00465  -0.0297   0.0083   1.0000
   6.250   0.8290   0.01114   0.00524  -0.0291   0.0074   1.0000
   6.500   0.8550   0.01133   0.00545  -0.0289   0.0072   1.0000
   6.750   0.8809   0.01154   0.00567  -0.0287   0.0063   1.0000
   7.000   0.9061   0.01184   0.00595  -0.0285   0.0041   1.0000
   7.250   0.9305   0.01229   0.00641  -0.0280   0.0028   1.0000
   7.500   0.9549   0.01276   0.00693  -0.0275   0.0024   1.0000
   7.750   0.9789   0.01326   0.00750  -0.0270   0.0021   1.0000
   8.000   1.0026   0.01382   0.00814  -0.0264   0.0018   1.0000
   8.250   1.0256   0.01447   0.00889  -0.0257   0.0015   1.0000
   8.500   1.0473   0.01533   0.00988  -0.0249   0.0013   1.0000
   8.750   1.0671   0.01648   0.01122  -0.0237   0.0011   1.0000
   9.000   1.0894   0.01715   0.01199  -0.0230   0.0011   1.0000
   9.250   1.1111   0.01789   0.01284  -0.0222   0.0010   1.0000
   9.500   1.1314   0.01883   0.01392  -0.0213   0.0010   1.0000
   9.750   1.1507   0.01990   0.01515  -0.0202   0.0009   1.0000
  10.000   1.1682   0.02119   0.01663  -0.0190   0.0009   1.0000
  10.250   1.1839   0.02268   0.01833  -0.0175   0.0008   1.0000
  10.500   1.1971   0.02446   0.02039  -0.0158   0.0008   1.0000
  10.750   1.2080   0.02639   0.02257  -0.0139   0.0007   1.0000
  11.000   1.2142   0.02876   0.02523  -0.0116   0.0007   1.0000
  11.250   1.2168   0.03125   0.02800  -0.0091   0.0007   1.0000
  11.500   1.2080   0.03435   0.03142  -0.0055   0.0007   1.0000
  11.750   1.1954   0.03692   0.03421  -0.0014   0.0007   1.0000
  12.000   1.1780   0.04008   0.03759   0.0016   0.0007   1.0000
  12.250   1.1587   0.04396   0.04168   0.0027   0.0007   1.0000
  12.500   1.1382   0.04892   0.04682   0.0017   0.0007   1.0000
  12.750   1.1178   0.05518   0.05326  -0.0019   0.0007   1.0000
  13.000   1.0974   0.06326   0.06149  -0.0078   0.0007   1.0000
  13.250   1.0716   0.07460   0.07299  -0.0162   0.0007   1.0000
  13.500   1.0453   0.08705   0.08554  -0.0240   0.0007   1.0000
  13.750   1.0062   0.10215   0.10069  -0.0317   0.0007   1.0000
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