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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 1,000,000
Max Cl/Cd: 149.16 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w121-il-1000000.txt
Download as CSV file: xf-fx77w121-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2672   0.08641   0.08294  -0.0335   0.4727   0.0107
  -8.500  -0.2625   0.08346   0.08000  -0.0351   0.4722   0.0122
  -8.250  -0.2620   0.07979   0.07635  -0.0372   0.4703   0.0125
  -8.000  -0.2636   0.07645   0.07303  -0.0383   0.4694   0.0112
  -7.250  -0.2763   0.06437   0.06097  -0.0452   0.4670   0.0130
  -7.000  -0.2737   0.06024   0.05680  -0.0466   0.4656   0.0130
  -6.750  -0.2686   0.05625   0.05274  -0.0475   0.4642   0.0130
  -6.500  -0.2634   0.05154   0.04794  -0.0480   0.4637   0.0130
  -6.250  -0.2597   0.04576   0.04201  -0.0477   0.4635   0.0131
  -6.000  -0.2509   0.04161   0.03771  -0.0468   0.4627   0.0131
  -5.750  -0.2423   0.03734   0.03325  -0.0453   0.4620   0.0131
  -5.500  -0.2521   0.03000   0.02552  -0.0416   0.4616   0.0118
  -5.250  -0.2701   0.01789   0.01211  -0.0330   0.4614   0.0111
  -5.000  -0.2491   0.01641   0.01037  -0.0315   0.4602   0.0114
  -4.750  -0.2269   0.01502   0.00873  -0.0302   0.4590   0.0117
  -4.500  -0.2024   0.01429   0.00786  -0.0293   0.4579   0.0121
  -4.250  -0.1769   0.01383   0.00729  -0.0287   0.4568   0.0127
  -4.000  -0.1536   0.01268   0.00594  -0.0275   0.4558   0.0135
  -3.750  -0.1295   0.01201   0.00517  -0.0266   0.4548   0.0141
  -3.500  -0.1032   0.01182   0.00496  -0.0262   0.4537   0.0151
  -3.250  -0.0768   0.01167   0.00477  -0.0257   0.4525   0.0162
  -3.000  -0.0510   0.01140   0.00444  -0.0252   0.4514   0.0172
  -2.750  -0.0263   0.01104   0.00399  -0.0244   0.4497   0.0186
  -2.500  -0.0009   0.01070   0.00364  -0.0237   0.4490   0.0202
  -2.250   0.0257   0.01055   0.00348  -0.0233   0.4484   0.0218
  -2.000   0.0530   0.01051   0.00344  -0.0231   0.4477   0.0238
  -1.750   0.0783   0.01019   0.00306  -0.0224   0.4470   0.0255
  -1.500   0.1041   0.00995   0.00282  -0.0219   0.4463   0.0285
  -1.250   0.1307   0.00984   0.00269  -0.0215   0.4454   0.0312
  -1.000   0.1576   0.00975   0.00258  -0.0212   0.4445   0.0330
  -0.750   0.1836   0.00956   0.00235  -0.0206   0.4436   0.0373
  -0.500   0.2103   0.00946   0.00225  -0.0203   0.4426   0.0433
  -0.250   0.2367   0.00933   0.00215  -0.0199   0.4415   0.0570
   0.000   0.2612   0.00902   0.00210  -0.0192   0.4407   0.1430
   0.250   0.2835   0.00854   0.00208  -0.0182   0.4398   0.3069
   0.500   0.3006   0.00779   0.00209  -0.0162   0.4389   0.5668
   0.750   0.4146   0.00712   0.00249  -0.0351   0.4374   0.9800
   1.000   0.4735   0.00741   0.00269  -0.0418   0.4358   0.9877
   1.250   0.5526   0.00761   0.00280  -0.0530   0.4345   0.9973
   1.500   0.5966   0.00751   0.00268  -0.0565   0.4333   1.0000
   1.750   0.6220   0.00754   0.00270  -0.0560   0.4324   1.0000
   2.000   0.6475   0.00757   0.00271  -0.0555   0.4314   1.0000
   2.250   0.6730   0.00760   0.00274  -0.0551   0.4303   1.0000
   2.500   0.6985   0.00764   0.00277  -0.0546   0.4291   1.0000
   2.750   0.7242   0.00768   0.00280  -0.0542   0.4279   1.0000
   3.000   0.7498   0.00771   0.00281  -0.0538   0.4262   1.0000
   3.250   0.7755   0.00775   0.00283  -0.0534   0.4247   1.0000
   3.500   0.8010   0.00781   0.00289  -0.0530   0.4230   1.0000
   3.750   0.8262   0.00800   0.00304  -0.0525   0.4200   1.0000
   4.000   0.8521   0.00800   0.00306  -0.0522   0.4190   1.0000
   4.250   0.8779   0.00801   0.00310  -0.0518   0.4177   1.0000
   4.500   0.9037   0.00802   0.00314  -0.0514   0.4160   1.0000
   4.750   0.9296   0.00806   0.00320  -0.0511   0.4145   1.0000
   5.000   0.9553   0.00811   0.00327  -0.0508   0.4130   1.0000
   5.250   0.9811   0.00816   0.00334  -0.0504   0.4116   1.0000
   5.500   1.0068   0.00822   0.00342  -0.0501   0.4100   1.0000
   5.750   1.0325   0.00829   0.00350  -0.0497   0.4083   1.0000
   6.000   1.0577   0.00844   0.00365  -0.0494   0.4057   1.0000
   6.250   1.0834   0.00850   0.00377  -0.0490   0.4042   1.0000
   6.500   1.1091   0.00853   0.00386  -0.0487   0.4027   1.0000
   6.750   1.1349   0.00856   0.00395  -0.0484   0.4007   1.0000
   7.000   1.1606   0.00857   0.00400  -0.0481   0.3978   1.0000
   7.500   1.2119   0.00853   0.00403  -0.0475   0.3879   1.0000
   7.750   1.2380   0.00848   0.00403  -0.0472   0.3803   1.0000
   8.000   1.2634   0.00847   0.00399  -0.0469   0.3633   1.0000
   8.250   1.2871   0.00867   0.00413  -0.0464   0.3416   1.0000
   8.500   1.3079   0.00913   0.00448  -0.0455   0.3114   1.0000
   8.750   1.3253   0.00988   0.00505  -0.0441   0.2742   1.0000
   9.000   1.3399   0.01087   0.00581  -0.0424   0.2314   1.0000
   9.250   1.3506   0.01213   0.00678  -0.0402   0.1828   1.0000
   9.500   1.3569   0.01362   0.00795  -0.0375   0.1296   1.0000
   9.750   1.3477   0.01599   0.00988  -0.0328   0.0599   1.0000
  10.000   1.3434   0.01775   0.01146  -0.0288   0.0260   1.0000
  10.250   1.3423   0.01919   0.01286  -0.0252   0.0132   1.0000
  10.500   1.3394   0.02022   0.01394  -0.0212   0.0108   1.0000
  10.750   1.3317   0.02208   0.01588  -0.0183   0.0090   1.0000
  11.000   1.3341   0.02422   0.01811  -0.0181   0.0080   1.0000
  11.250   1.3366   0.02679   0.02078  -0.0185   0.0078   1.0000
  11.500   1.3384   0.02950   0.02356  -0.0189   0.0074   1.0000
  11.750   1.3285   0.03347   0.02763  -0.0192   0.0062   1.0000
  12.000   1.3268   0.03642   0.03066  -0.0192   0.0058   1.0000
  12.250   1.3231   0.03951   0.03385  -0.0193   0.0061   1.0000
  12.500   1.3314   0.04128   0.03564  -0.0193   0.0055   1.0000
  12.750   1.3264   0.04449   0.03893  -0.0193   0.0052   1.0000
  13.000   1.3230   0.04752   0.04203  -0.0193   0.0050   1.0000
  13.250   1.3149   0.05106   0.04563  -0.0194   0.0044   1.0000
  13.500   1.3120   0.05409   0.04875  -0.0194   0.0045   1.0000
  13.750   1.3116   0.05697   0.05168  -0.0196   0.0045   1.0000
  14.000   1.2932   0.06212   0.05697  -0.0201   0.0042   1.0000
  14.250   1.2875   0.06584   0.06077  -0.0206   0.0040   1.0000
  14.500   1.2908   0.06845   0.06344  -0.0209   0.0038   1.0000
  14.750   1.2948   0.07099   0.06603  -0.0213   0.0039   1.0000
  15.000   1.2867   0.07514   0.07027  -0.0219   0.0040   1.0000
  15.250   1.2796   0.07930   0.07452  -0.0226   0.0039   1.0000
  15.500   1.2874   0.08142   0.07667  -0.0230   0.0036   1.0000
  15.750   1.2763   0.08616   0.08152  -0.0238   0.0037   1.0000
  16.000   1.2789   0.08907   0.08449  -0.0244   0.0036   1.0000
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