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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 500,000
Max Cl/Cd: 114.35 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w121-il-500000-n5.txt
Download as CSV file: xf-fx77w121-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-121                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2840   0.08566   0.08150  -0.0314   0.4726   0.0086
  -8.500  -0.2829   0.08228   0.07814  -0.0329   0.4715   0.0085
  -8.250  -0.2837   0.07874   0.07462  -0.0345   0.4701   0.0083
  -8.000  -0.2906   0.07456   0.07048  -0.0367   0.4692   0.0085
  -7.750  -0.3001   0.07089   0.06685  -0.0381   0.4684   0.0083
  -7.500  -0.3042   0.06746   0.06340  -0.0394   0.4673   0.0079
  -7.250  -0.3109   0.06172   0.05763  -0.0422   0.4667   0.0084
  -7.000  -0.3106   0.05685   0.05269  -0.0438   0.4657   0.0082
  -6.500  -0.3080   0.04512   0.04063  -0.0449   0.4638   0.0084
  -6.250  -0.3534   0.02422   0.01832  -0.0374   0.4649   0.0092
  -6.000  -0.3394   0.02122   0.01478  -0.0351   0.4636   0.0094
  -5.750  -0.3222   0.01893   0.01208  -0.0332   0.4623   0.0097
  -5.500  -0.2974   0.01871   0.01182  -0.0327   0.4607   0.0102
  -5.250  -0.2737   0.01794   0.01089  -0.0319   0.4593   0.0106
  -5.000  -0.2504   0.01693   0.00965  -0.0309   0.4580   0.0109
  -4.750  -0.2261   0.01615   0.00871  -0.0301   0.4567   0.0115
  -4.500  -0.2017   0.01534   0.00770  -0.0292   0.4555   0.0120
  -4.250  -0.1766   0.01473   0.00693  -0.0285   0.4542   0.0127
  -4.000  -0.1518   0.01414   0.00620  -0.0277   0.4530   0.0134
  -3.750  -0.1269   0.01367   0.00565  -0.0271   0.4516   0.0139
  -3.500  -0.1009   0.01345   0.00538  -0.0266   0.4503   0.0149
  -3.250  -0.0746   0.01330   0.00518  -0.0262   0.4491   0.0163
  -3.000  -0.0485   0.01302   0.00484  -0.0257   0.4483   0.0175
  -2.750  -0.0233   0.01260   0.00438  -0.0250   0.4474   0.0190
  -2.500   0.0027   0.01237   0.00412  -0.0245   0.4464   0.0203
  -2.250   0.0289   0.01218   0.00390  -0.0241   0.4455   0.0221
  -2.000   0.0555   0.01206   0.00374  -0.0237   0.4445   0.0240
  -1.750   0.0809   0.01175   0.00339  -0.0231   0.4434   0.0263
  -1.500   0.1071   0.01158   0.00320  -0.0227   0.4423   0.0285
  -1.250   0.1336   0.01145   0.00305  -0.0223   0.4410   0.0315
  -1.000   0.1601   0.01135   0.00290  -0.0219   0.4400   0.0336
  -0.750   0.1863   0.01120   0.00273  -0.0215   0.4392   0.0387
  -0.500   0.2128   0.01112   0.00264  -0.0211   0.4382   0.0454
  -0.250   0.2390   0.01101   0.00256  -0.0207   0.4373   0.0630
   0.000   0.2647   0.01084   0.00251  -0.0203   0.4365   0.1067
   0.250   0.2893   0.01059   0.00249  -0.0197   0.4355   0.1952
   0.500   0.3117   0.01014   0.00250  -0.0188   0.4344   0.3559
   0.750   0.3308   0.00954   0.00250  -0.0171   0.4337   0.5539
   1.000   0.5063   0.00895   0.00296  -0.0490   0.4318   0.9948
   1.250   0.5555   0.00897   0.00292  -0.0537   0.4307   1.0000
   1.500   0.5809   0.00902   0.00294  -0.0532   0.4298   1.0000
   1.750   0.6064   0.00908   0.00297  -0.0527   0.4288   1.0000
   2.000   0.6319   0.00913   0.00300  -0.0523   0.4277   1.0000
   2.250   0.6574   0.00919   0.00303  -0.0519   0.4262   1.0000
   2.500   0.6830   0.00925   0.00307  -0.0514   0.4250   1.0000
   2.750   0.7085   0.00931   0.00311  -0.0510   0.4235   1.0000
   3.000   0.7341   0.00939   0.00317  -0.0506   0.4222   1.0000
   3.250   0.7596   0.00950   0.00324  -0.0502   0.4210   1.0000
   3.500   0.7851   0.00961   0.00334  -0.0498   0.4197   1.0000
   3.750   0.8108   0.00966   0.00343  -0.0494   0.4183   1.0000
   4.000   0.8363   0.00971   0.00352  -0.0490   0.4165   1.0000
   4.250   0.8619   0.00977   0.00360  -0.0486   0.4144   1.0000
   4.500   0.8874   0.00983   0.00370  -0.0482   0.4122   1.0000
   4.750   0.9129   0.00991   0.00379  -0.0478   0.4105   1.0000
   5.000   0.9383   0.00998   0.00386  -0.0474   0.4081   1.0000
   5.250   0.9635   0.01008   0.00395  -0.0470   0.4056   1.0000
   5.500   0.9889   0.01017   0.00410  -0.0466   0.4037   1.0000
   5.750   1.0144   0.01025   0.00426  -0.0463   0.4019   1.0000
   6.000   1.0398   0.01035   0.00441  -0.0459   0.4000   1.0000
   6.250   1.0651   0.01044   0.00457  -0.0455   0.3978   1.0000
   6.500   1.0904   0.01053   0.00472  -0.0452   0.3957   1.0000
   6.750   1.1156   0.01062   0.00484  -0.0447   0.3931   1.0000
   7.000   1.1405   0.01074   0.00499  -0.0443   0.3909   1.0000
   7.250   1.1656   0.01083   0.00520  -0.0440   0.3880   1.0000
   7.500   1.1908   0.01093   0.00541  -0.0436   0.3847   1.0000
   7.750   1.2157   0.01101   0.00556  -0.0432   0.3804   1.0000
   8.000   1.2406   0.01105   0.00567  -0.0428   0.3726   1.0000
   8.250   1.2647   0.01106   0.00568  -0.0422   0.3541   1.0000
   8.500   1.2855   0.01137   0.00588  -0.0413   0.3247   1.0000
   8.750   1.2998   0.01228   0.00653  -0.0396   0.2790   1.0000
   9.000   1.3097   0.01358   0.00756  -0.0374   0.2290   1.0000
   9.250   1.3176   0.01496   0.00870  -0.0350   0.1844   1.0000
   9.500   1.3201   0.01662   0.01007  -0.0320   0.1352   1.0000
   9.750   1.3132   0.01868   0.01184  -0.0280   0.0864   1.0000
  10.000   1.3073   0.02050   0.01352  -0.0242   0.0569   1.0000
  10.250   1.2931   0.02229   0.01528  -0.0195   0.0408   1.0000
  10.500   1.2761   0.02569   0.01869  -0.0181   0.0251   1.0000
  10.750   1.2712   0.02899   0.02204  -0.0185   0.0187   1.0000
  11.000   1.2692   0.03205   0.02516  -0.0188   0.0149   1.0000
  11.250   1.2669   0.03508   0.02826  -0.0189   0.0127   1.0000
  11.500   1.2671   0.03777   0.03103  -0.0189   0.0117   1.0000
  11.750   1.2623   0.04095   0.03426  -0.0189   0.0098   1.0000
  12.000   1.2588   0.04399   0.03737  -0.0189   0.0080   1.0000
  12.250   1.2588   0.04664   0.04011  -0.0188   0.0083   1.0000
  12.500   1.2590   0.04928   0.04282  -0.0188   0.0079   1.0000
  12.750   1.2549   0.05238   0.04597  -0.0188   0.0069   1.0000
  13.000   1.2489   0.05575   0.04942  -0.0188   0.0062   1.0000
  13.250   1.2505   0.05840   0.05213  -0.0190   0.0058   1.0000
  13.500   1.2502   0.06133   0.05514  -0.0192   0.0056   1.0000
  13.750   1.2497   0.06436   0.05825  -0.0196   0.0055   1.0000
  14.000   1.2499   0.06733   0.06129  -0.0199   0.0048   1.0000
  14.250   1.2495   0.07041   0.06447  -0.0203   0.0048   1.0000
  14.500   1.2471   0.07381   0.06792  -0.0208   0.0043   1.0000
  14.750   1.2484   0.07679   0.07100  -0.0212   0.0046   1.0000
  15.000   1.2447   0.08047   0.07476  -0.0218   0.0045   1.0000
  15.250   1.2412   0.08416   0.07851  -0.0225   0.0042   1.0000
  15.500   1.2371   0.08803   0.08247  -0.0233   0.0040   1.0000
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