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FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 60-157 AIRFOIL (fx60157-il)
Reynolds number: 50,000
Max Cl/Cd: 28.8 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60157-il-50000.txt
Download as CSV file: xf-fx60157-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-157 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3897   0.11891   0.11231  -0.0189   1.0000   0.3598
  -9.250  -0.5394   0.09705   0.09087  -0.0412   1.0000   0.1712
  -9.000  -0.5758   0.08905   0.08291  -0.0437   1.0000   0.1497
  -8.750  -0.5713   0.07812   0.07243  -0.0424   1.0000   0.1415
  -8.500  -0.5990   0.07417   0.06846  -0.0402   1.0000   0.1367
  -8.250  -0.6248   0.07005   0.06432  -0.0381   1.0000   0.1336
  -8.000  -0.7368   0.07069   0.06394  -0.0372   1.0000   0.1242
  -7.750  -0.7370   0.06636   0.05948  -0.0357   1.0000   0.1212
  -7.500  -0.7413   0.06194   0.05472  -0.0344   1.0000   0.1182
  -7.250  -0.7415   0.05757   0.04984  -0.0334   1.0000   0.1162
  -7.000  -0.7336   0.05396   0.04583  -0.0324   1.0000   0.1172
  -6.750  -0.7215   0.05064   0.04209  -0.0316   1.0000   0.1192
  -6.500  -0.7061   0.04758   0.03849  -0.0310   1.0000   0.1226
  -6.250  -0.6872   0.04475   0.03499  -0.0305   1.0000   0.1259
  -6.000  -0.6680   0.04224   0.03256  -0.0295   1.0000   0.1317
  -5.750  -0.6462   0.04007   0.03001  -0.0285   1.0000   0.1353
  -5.500  -0.6242   0.03824   0.02779  -0.0274   1.0000   0.1409
  -5.250  -0.6041   0.03671   0.02633  -0.0259   1.0000   0.1487
  -5.000  -0.5830   0.03548   0.02492  -0.0238   1.0000   0.1556
  -4.750  -0.5645   0.03449   0.02408  -0.0212   1.0000   0.1659
  -4.500  -0.5468   0.03362   0.02329  -0.0188   1.0000   0.1823
  -4.250  -0.5310   0.03254   0.02247  -0.0164   1.0000   0.2049
  -4.000  -0.5151   0.03072   0.02132  -0.0152   1.0000   0.2611
  -3.750  -0.5286   0.03028   0.02384  -0.0034   1.0000   0.5835
  -3.500  -0.5338   0.03419   0.02752   0.0092   1.0000   0.6996
  -3.250  -0.5335   0.03626   0.02937   0.0182   1.0000   0.7427
  -3.000  -0.5304   0.03769   0.03063   0.0263   1.0000   0.7736
  -2.750  -0.5229   0.03876   0.03152   0.0333   1.0000   0.8047
  -2.500  -0.2890   0.04477   0.03635   0.0115   1.0000   0.9276
  -2.250  -0.2373   0.04427   0.03554   0.0053   1.0000   0.9490
  -2.000  -0.1897   0.04380   0.03481  -0.0007   1.0000   0.9660
  -1.750  -0.1424   0.04353   0.03429  -0.0069   1.0000   0.9819
  -1.500  -0.0911   0.04332   0.03387  -0.0141   1.0000   0.9953
  -1.250  -0.0700   0.04323   0.03365  -0.0157   1.0000   1.0000
  -1.000  -0.0679   0.04308   0.03345  -0.0136   1.0000   1.0000
  -0.750  -0.0657   0.04298   0.03330  -0.0116   1.0000   1.0000
  -0.500  -0.0637   0.04292   0.03319  -0.0095   1.0000   1.0000
  -0.250  -0.0617   0.04289   0.03313  -0.0075   1.0000   1.0000
   0.000  -0.0599   0.04291   0.03311  -0.0054   1.0000   1.0000
   0.250  -0.0581   0.04296   0.03312  -0.0033   1.0000   1.0000
   0.500  -0.0566   0.04303   0.03317  -0.0013   1.0000   1.0000
   0.750  -0.0552   0.04313   0.03325   0.0008   1.0000   1.0000
   1.000  -0.0540   0.04326   0.03336   0.0028   1.0000   1.0000
   1.250  -0.0529   0.04340   0.03348   0.0049   1.0000   1.0000
   1.500  -0.0520   0.04356   0.03362   0.0069   1.0000   1.0000
   1.750   0.0304   0.04587   0.03586  -0.0061   0.9702   1.0000
   2.000   0.0727   0.04669   0.03664  -0.0110   0.9461   1.0000
   2.250   0.1148   0.04769   0.03761  -0.0156   0.9259   1.0000
   2.500   0.1424   0.04811   0.03802  -0.0175   0.9049   1.0000
   2.750   0.1687   0.04855   0.03846  -0.0189   0.8853   1.0000
   3.000   0.1965   0.04900   0.03890  -0.0204   0.8665   1.0000
   3.250   0.2215   0.04943   0.03935  -0.0213   0.8492   1.0000
   3.500   0.2435   0.04984   0.03977  -0.0217   0.8327   1.0000
   3.750   0.2663   0.05019   0.04014  -0.0221   0.8161   1.0000
   4.000   0.2940   0.05044   0.04042  -0.0229   0.7988   1.0000
   4.250   0.3230   0.05057   0.04059  -0.0236   0.7817   1.0000
   4.500   0.3378   0.05070   0.04074  -0.0224   0.7641   1.0000
   4.750   0.3543   0.05087   0.04096  -0.0214   0.7477   1.0000
   5.000   0.3736   0.05103   0.04116  -0.0207   0.7319   1.0000
   5.250   0.3930   0.05120   0.04140  -0.0200   0.7155   1.0000
   5.500   0.4119   0.05143   0.04168  -0.0193   0.6979   1.0000
   5.750   0.4349   0.05167   0.04199  -0.0192   0.6802   1.0000
   6.000   0.4628   0.05179   0.04220  -0.0196   0.6619   1.0000
   6.250   0.4940   0.05183   0.04234  -0.0202   0.6442   1.0000
   6.500   0.5258   0.05194   0.04256  -0.0210   0.6274   1.0000
   6.750   0.5586   0.05201   0.04275  -0.0217   0.6107   1.0000
   7.000   0.5916   0.05207   0.04295  -0.0225   0.5941   1.0000
   7.250   0.6301   0.05153   0.04257  -0.0231   0.5775   1.0000
   7.500   0.7464   0.04406   0.03538  -0.0263   0.5696   1.0000
   7.750   0.7489   0.04594   0.03734  -0.0248   0.5473   1.0000
   8.000   0.8385   0.04138   0.03301  -0.0279   0.5313   1.0000
   8.250   0.9714   0.03632   0.02803  -0.0373   0.5026   1.0000
   8.500   0.9842   0.03716   0.02897  -0.0354   0.4799   1.0000
   8.750   1.0456   0.03669   0.02844  -0.0392   0.4511   1.0000
   9.000   1.0613   0.03783   0.02968  -0.0379   0.4307   1.0000
   9.250   1.0892   0.03889   0.03082  -0.0383   0.4100   1.0000
   9.500   1.1401   0.03959   0.03140  -0.0415   0.3868   1.0000
   9.750   1.1526   0.04098   0.03292  -0.0399   0.3688   1.0000
  10.000   1.1664   0.04226   0.03431  -0.0385   0.3504   1.0000
  10.250   1.1826   0.04364   0.03578  -0.0375   0.3325   1.0000
  10.500   1.2002   0.04530   0.03755  -0.0368   0.3164   1.0000
  10.750   1.2177   0.04705   0.03941  -0.0361   0.3011   1.0000
  11.000   1.2332   0.04868   0.04113  -0.0352   0.2852   1.0000
  11.250   1.2449   0.05012   0.04263  -0.0337   0.2687   1.0000
  11.500   1.2529   0.05145   0.04401  -0.0318   0.2526   1.0000
  11.750   1.2613   0.05293   0.04553  -0.0301   0.2369   1.0000
  12.000   1.2714   0.05462   0.04725  -0.0287   0.2216   1.0000
  12.250   1.2807   0.05648   0.04915  -0.0274   0.2068   1.0000
  12.500   1.2512   0.06021   0.05330  -0.0232   0.2023   1.0000
  13.000   1.2610   0.06387   0.05693  -0.0204   0.1750   1.0000
  13.250   1.2280   0.06869   0.06213  -0.0178   0.1726   1.0000
  13.500   1.1917   0.07458   0.06834  -0.0164   0.1714   1.0000
  13.750   1.1454   0.08264   0.07668  -0.0167   0.1736   1.0000
  14.000   1.0977   0.09243   0.08664  -0.0191   0.1761   1.0000
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