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FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 68-H-120 (fx68h120-il)
Reynolds number: 500,000
Max Cl/Cd: 74.87 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx68h120-il-500000.txt
Download as CSV file: xf-fx68h120-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 68-H-120                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5066   0.09440   0.09245  -0.0229   1.0000   0.0178
 -11.000  -0.4945   0.09329   0.09134  -0.0240   1.0000   0.0185
 -10.500  -0.6665   0.04226   0.03944  -0.0646   0.9678   0.0108
 -10.250  -0.6876   0.03938   0.03630  -0.0615   0.9498   0.0107
 -10.000  -0.7036   0.03669   0.03335  -0.0576   0.9390   0.0106
  -9.500  -0.7108   0.03124   0.02728  -0.0517   0.9248   0.0106
  -9.250  -0.7041   0.02919   0.02493  -0.0493   0.9198   0.0107
  -9.000  -0.6927   0.02740   0.02287  -0.0474   0.9158   0.0109
  -8.750  -0.6773   0.02573   0.02096  -0.0459   0.9115   0.0110
  -8.500  -0.6611   0.02440   0.01939  -0.0443   0.9076   0.0113
  -8.250  -0.6484   0.02216   0.01687  -0.0421   0.9041   0.0114
  -8.000  -0.6322   0.02003   0.01452  -0.0406   0.9007   0.0118
  -7.750  -0.6129   0.01865   0.01301  -0.0394   0.8972   0.0123
  -7.500  -0.5922   0.01769   0.01193  -0.0383   0.8941   0.0128
  -7.250  -0.5699   0.01714   0.01132  -0.0373   0.8913   0.0138
  -7.000  -0.5473   0.01646   0.01054  -0.0364   0.8886   0.0145
  -6.750  -0.5232   0.01570   0.00968  -0.0357   0.8855   0.0152
  -6.500  -0.4991   0.01507   0.00896  -0.0350   0.8825   0.0160
  -6.250  -0.4748   0.01458   0.00837  -0.0342   0.8797   0.0166
  -6.000  -0.4537   0.01364   0.00728  -0.0328   0.8771   0.0185
  -5.750  -0.4293   0.01312   0.00671  -0.0320   0.8748   0.0211
  -5.500  -0.4033   0.01258   0.00610  -0.0316   0.8718   0.0276
  -5.250  -0.3817   0.01156   0.00547  -0.0307   0.8685   0.0880
  -5.000  -0.3563   0.01134   0.00530  -0.0300   0.8648   0.1121
  -4.750  -0.3312   0.01120   0.00512  -0.0292   0.8599   0.1237
  -4.500  -0.3050   0.01104   0.00493  -0.0286   0.8529   0.1334
  -4.250  -0.2800   0.01085   0.00471  -0.0277   0.8483   0.1414
  -4.000  -0.2526   0.01076   0.00459  -0.0275   0.8429   0.1522
  -3.750  -0.2254   0.01068   0.00449  -0.0271   0.8379   0.1629
  -3.500  -0.1999   0.01044   0.00425  -0.0264   0.8341   0.1707
  -3.250  -0.1722   0.01034   0.00410  -0.0263   0.8295   0.1772
  -3.000  -0.1459   0.01008   0.00386  -0.0258   0.8246   0.1843
  -2.750  -0.1194   0.00991   0.00364  -0.0253   0.8203   0.1910
  -2.500  -0.0927   0.00969   0.00347  -0.0250   0.8150   0.1999
  -2.250  -0.0658   0.00950   0.00328  -0.0246   0.8097   0.2097
  -2.000  -0.0396   0.00929   0.00306  -0.0240   0.8049   0.2226
  -1.750  -0.0129   0.00903   0.00291  -0.0237   0.7973   0.2428
  -1.500   0.0126   0.00873   0.00270  -0.0230   0.7904   0.2783
  -1.250   0.0378   0.00834   0.00256  -0.0224   0.7817   0.3412
  -1.000   0.0614   0.00788   0.00241  -0.0215   0.7738   0.4338
  -0.750   0.0835   0.00738   0.00228  -0.0203   0.7648   0.5452
  -0.500   0.1028   0.00682   0.00220  -0.0184   0.7548   0.6768
  -0.250   0.1248   0.00623   0.00219  -0.0165   0.7439   0.8381
   0.000   0.1844   0.00621   0.00230  -0.0226   0.7268   0.9246
   0.250   0.2259   0.00632   0.00231  -0.0251   0.7069   0.9459
   0.500   0.2622   0.00647   0.00234  -0.0266   0.6774   0.9590
   0.750   0.2968   0.00675   0.00236  -0.0277   0.6204   0.9700
   1.000   0.3401   0.00730   0.00246  -0.0311   0.5340   0.9760
   1.250   0.3748   0.00776   0.00263  -0.0327   0.4820   0.9832
   1.500   0.4175   0.00808   0.00272  -0.0361   0.4420   0.9871
   1.750   0.4584   0.00837   0.00283  -0.0390   0.4095   0.9923
   2.000   0.4997   0.00859   0.00289  -0.0421   0.3815   0.9965
   2.250   0.5406   0.00878   0.00293  -0.0451   0.3560   1.0000
   2.500   0.5645   0.00898   0.00301  -0.0445   0.3367   1.0000
   2.750   0.5884   0.00915   0.00310  -0.0439   0.3191   1.0000
   3.000   0.6123   0.00934   0.00320  -0.0433   0.3028   1.0000
   3.250   0.6361   0.00953   0.00330  -0.0426   0.2878   1.0000
   3.500   0.6598   0.00972   0.00344  -0.0419   0.2737   1.0000
   3.750   0.6834   0.00993   0.00357  -0.0412   0.2605   1.0000
   4.000   0.7067   0.01015   0.00373  -0.0405   0.2486   1.0000
   4.500   0.7530   0.01061   0.00409  -0.0390   0.2282   1.0000
   4.750   0.7758   0.01085   0.00429  -0.0381   0.2201   1.0000
   5.000   0.7985   0.01110   0.00450  -0.0372   0.2125   1.0000
   5.250   0.8211   0.01134   0.00472  -0.0363   0.2057   1.0000
   5.500   0.8433   0.01160   0.00493  -0.0354   0.1973   1.0000
   5.750   0.8661   0.01180   0.00515  -0.0346   0.1904   1.0000
   6.000   0.8879   0.01208   0.00538  -0.0336   0.1837   1.0000
   6.250   0.9104   0.01228   0.00558  -0.0327   0.1764   1.0000
   6.500   0.9319   0.01256   0.00583  -0.0316   0.1696   1.0000
   6.750   0.9543   0.01275   0.00603  -0.0307   0.1620   1.0000
   7.000   0.9756   0.01303   0.00623  -0.0297   0.1459   1.0000
   7.250   0.9940   0.01356   0.00652  -0.0283   0.1152   1.0000
   7.500   0.9944   0.01559   0.00795  -0.0244   0.0174   1.0000
   7.750   1.0124   0.01612   0.00854  -0.0227   0.0130   1.0000
   8.000   1.0306   0.01658   0.00909  -0.0211   0.0116   1.0000
   8.250   1.0476   0.01714   0.00975  -0.0193   0.0106   1.0000
   8.500   1.0630   0.01780   0.01052  -0.0173   0.0098   1.0000
   8.750   1.0749   0.01870   0.01156  -0.0148   0.0091   1.0000
   9.000   1.0840   0.01973   0.01274  -0.0120   0.0088   1.0000
   9.250   1.0881   0.02079   0.01392  -0.0084   0.0085   1.0000
   9.500   1.0949   0.02154   0.01475  -0.0053   0.0083   1.0000
   9.750   1.0988   0.02257   0.01587  -0.0021   0.0083   1.0000
  10.000   1.1020   0.02376   0.01716   0.0009   0.0083   1.0000
  10.250   1.1050   0.02507   0.01857   0.0036   0.0082   1.0000
  10.500   1.1072   0.02653   0.02013   0.0061   0.0081   1.0000
  10.750   1.1068   0.02828   0.02198   0.0084   0.0082   1.0000
  11.000   1.1055   0.03022   0.02402   0.0106   0.0082   1.0000
  11.250   1.1037   0.03233   0.02622   0.0124   0.0082   1.0000
  11.500   1.1013   0.03465   0.02862   0.0139   0.0083   1.0000
  11.750   1.0957   0.03740   0.03144   0.0154   0.0084   1.0000
  12.000   1.0904   0.04033   0.03440   0.0170   0.0087   1.0000
  12.250   1.0964   0.04220   0.03636   0.0175   0.0088   1.0000
  12.500   1.1024   0.04417   0.03842   0.0178   0.0089   1.0000
  12.750   1.1072   0.04636   0.04069   0.0180   0.0091   1.0000
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