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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.98 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w153-il-1000000-n5.txt
Download as CSV file: xf-fx77w153-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-W-153 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.9075   0.03948   0.03547  -0.0397   0.4740   0.0092
 -12.000  -0.9177   0.03601   0.03175  -0.0378   0.4696   0.0092
 -11.750  -0.9149   0.03339   0.02889  -0.0363   0.4631   0.0092
 -11.500  -0.9071   0.03118   0.02644  -0.0350   0.4568   0.0092
 -11.250  -0.8947   0.02940   0.02446  -0.0337   0.4495   0.0092
 -11.000  -0.8787   0.02801   0.02289  -0.0327   0.4417   0.0093
 -10.750  -0.8608   0.02679   0.02150  -0.0317   0.4351   0.0093
 -10.500  -0.8412   0.02575   0.02031  -0.0308   0.4285   0.0094
 -10.250  -0.8201   0.02488   0.01930  -0.0301   0.4234   0.0094
 -10.000  -0.7986   0.02402   0.01831  -0.0293   0.4191   0.0095
  -9.750  -0.7762   0.02325   0.01742  -0.0286   0.4149   0.0095
  -9.500  -0.7539   0.02243   0.01646  -0.0279   0.4108   0.0096
  -9.250  -0.7328   0.02136   0.01524  -0.0270   0.4079   0.0096
  -9.000  -0.7120   0.02017   0.01386  -0.0260   0.4053   0.0097
  -8.750  -0.6897   0.01918   0.01271  -0.0252   0.4024   0.0097
  -8.500  -0.6663   0.01837   0.01176  -0.0245   0.3993   0.0098
  -8.250  -0.6421   0.01768   0.01095  -0.0239   0.3963   0.0098
  -8.000  -0.6173   0.01706   0.01022  -0.0233   0.3934   0.0098
  -7.750  -0.5921   0.01647   0.00953  -0.0228   0.3916   0.0099
  -7.500  -0.5667   0.01592   0.00890  -0.0222   0.3896   0.0099
  -7.250  -0.5408   0.01542   0.00832  -0.0218   0.3873   0.0099
  -7.000  -0.5148   0.01495   0.00777  -0.0213   0.3849   0.0100
  -6.750  -0.4885   0.01453   0.00728  -0.0209   0.3825   0.0100
  -6.500  -0.4619   0.01414   0.00681  -0.0205   0.3804   0.0101
  -6.000  -0.4082   0.01344   0.00600  -0.0199   0.3769   0.0102
  -5.750  -0.3811   0.01313   0.00564  -0.0196   0.3757   0.0103
  -5.500  -0.3538   0.01283   0.00530  -0.0193   0.3744   0.0104
  -5.250  -0.3264   0.01256   0.00498  -0.0190   0.3729   0.0105
  -5.000  -0.2989   0.01231   0.00469  -0.0188   0.3716   0.0107
  -4.750  -0.2712   0.01208   0.00442  -0.0186   0.3704   0.0108
  -4.500  -0.2435   0.01186   0.00417  -0.0184   0.3694   0.0110
  -4.250  -0.2156   0.01167   0.00394  -0.0182   0.3685   0.0112
  -4.000  -0.1877   0.01148   0.00372  -0.0180   0.3676   0.0114
  -3.750  -0.1597   0.01132   0.00352  -0.0179   0.3667   0.0117
  -3.500  -0.1316   0.01117   0.00334  -0.0177   0.3659   0.0120
  -3.250  -0.1035   0.01103   0.00318  -0.0176   0.3650   0.0123
  -3.000  -0.0753   0.01090   0.00304  -0.0175   0.3641   0.0130
  -2.750  -0.0471   0.01078   0.00292  -0.0174   0.3631   0.0142
  -2.250   0.0098   0.01064   0.00283  -0.0173   0.3614   0.0213
  -2.000   0.0385   0.01060   0.00277  -0.0173   0.3611   0.0225
  -1.750   0.0669   0.01052   0.00270  -0.0173   0.3607   0.0237
  -1.500   0.0955   0.01046   0.00264  -0.0173   0.3602   0.0248
  -1.250   0.1241   0.01040   0.00258  -0.0173   0.3595   0.0257
  -1.000   0.1528   0.01036   0.00253  -0.0174   0.3587   0.0265
  -0.750   0.1813   0.01028   0.00245  -0.0174   0.3578   0.0274
  -0.500   0.2097   0.01020   0.00238  -0.0174   0.3567   0.0287
  -0.250   0.2382   0.01014   0.00232  -0.0174   0.3555   0.0298
   0.000   0.2668   0.01010   0.00227  -0.0174   0.3542   0.0305
   0.250   0.2954   0.01008   0.00223  -0.0175   0.3529   0.0311
   0.500   0.3240   0.01005   0.00220  -0.0175   0.3520   0.0323
   0.750   0.3525   0.01002   0.00219  -0.0176   0.3513   0.0349
   1.250   0.4094   0.00999   0.00220  -0.0177   0.3495   0.0504
   1.500   0.4378   0.00998   0.00221  -0.0177   0.3487   0.0585
   1.750   0.4660   0.00994   0.00224  -0.0177   0.3478   0.0852
   2.000   0.4939   0.00989   0.00228  -0.0178   0.3468   0.1194
   2.250   0.5216   0.00981   0.00232  -0.0178   0.3460   0.1727
   2.500   0.5484   0.00954   0.00235  -0.0177   0.3455   0.2846
   2.750   0.5746   0.00922   0.00239  -0.0175   0.3449   0.4094
   3.000   0.5997   0.00886   0.00243  -0.0171   0.3443   0.5494
   3.250   0.6218   0.00836   0.00248  -0.0160   0.3437   0.7266
   3.500   0.6584   0.00791   0.00272  -0.0175   0.3429   0.9491
   3.750   0.6936   0.00804   0.00285  -0.0190   0.3420   0.9682
   4.000   0.7214   0.00815   0.00295  -0.0189   0.3409   0.9788
   4.250   0.7698   0.00828   0.00307  -0.0233   0.3395   0.9839
   4.500   0.8170   0.00842   0.00320  -0.0275   0.3381   0.9908
   4.750   0.8579   0.00851   0.00328  -0.0303   0.3364   0.9935
   5.000   0.9008   0.00858   0.00333  -0.0337   0.3345   0.9957
   5.250   0.9378   0.00867   0.00340  -0.0357   0.3328   0.9975
   5.500   0.9706   0.00878   0.00350  -0.0369   0.3310   0.9985
   5.750   1.0023   0.00885   0.00358  -0.0379   0.3299   0.9992
   6.000   1.0347   0.00890   0.00366  -0.0389   0.3287   0.9999
   6.250   1.0620   0.00894   0.00373  -0.0389   0.3261   1.0000
   6.500   1.0887   0.00898   0.00377  -0.0388   0.3205   1.0000
   6.750   1.1151   0.00904   0.00380  -0.0386   0.3121   1.0000
   7.000   1.1406   0.00920   0.00386  -0.0384   0.2959   1.0000
   7.250   1.1652   0.00947   0.00406  -0.0380   0.2839   1.0000
   7.500   1.1898   0.00973   0.00428  -0.0376   0.2754   1.0000
   7.750   1.2146   0.00994   0.00448  -0.0373   0.2702   1.0000
   8.000   1.2392   0.01016   0.00469  -0.0369   0.2615   1.0000
   8.250   1.2625   0.01050   0.00497  -0.0364   0.2499   1.0000
   8.500   1.2848   0.01091   0.00531  -0.0357   0.2378   1.0000
   8.750   1.3070   0.01129   0.00566  -0.0351   0.2292   1.0000
   9.000   1.3301   0.01157   0.00594  -0.0345   0.2226   1.0000
   9.250   1.3508   0.01203   0.00634  -0.0336   0.2120   1.0000
   9.500   1.3708   0.01251   0.00677  -0.0326   0.1970   1.0000
   9.750   1.3884   0.01314   0.00731  -0.0313   0.1819   1.0000
  10.000   1.4066   0.01367   0.00779  -0.0301   0.1718   1.0000
  10.250   1.4261   0.01408   0.00820  -0.0290   0.1648   1.0000
  10.500   1.4391   0.01486   0.00890  -0.0271   0.1454   1.0000
  10.750   1.4467   0.01588   0.00979  -0.0245   0.1267   1.0000
  11.000   1.4462   0.01720   0.01100  -0.0208   0.1005   1.0000
  11.250   1.4495   0.01821   0.01197  -0.0177   0.0901   1.0000
  11.500   1.4516   0.01909   0.01285  -0.0144   0.0821   1.0000
  11.750   1.4486   0.02047   0.01424  -0.0112   0.0716   1.0000
  12.000   1.4391   0.02299   0.01675  -0.0094   0.0599   1.0000
  12.250   1.4360   0.02596   0.01979  -0.0098   0.0531   1.0000
  12.500   1.4300   0.02997   0.02386  -0.0113   0.0477   1.0000
  12.750   1.4245   0.03396   0.02794  -0.0126   0.0433   1.0000
  13.000   1.4027   0.03968   0.03374  -0.0138   0.0360   1.0000
  13.250   1.3807   0.04514   0.03927  -0.0146   0.0319   1.0000
  13.500   1.3668   0.04954   0.04375  -0.0151   0.0303   1.0000
  13.750   1.3521   0.05403   0.04831  -0.0156   0.0284   1.0000
  14.000   1.3378   0.05844   0.05279  -0.0161   0.0266   1.0000
  14.250   1.3305   0.06215   0.05657  -0.0165   0.0251   1.0000
  14.500   1.3215   0.06619   0.06066  -0.0171   0.0221   1.0000
  14.750   1.3073   0.07098   0.06549  -0.0180   0.0167   1.0000
  15.000   1.2982   0.07517   0.06970  -0.0187   0.0144   1.0000
  15.250   1.2941   0.07880   0.07338  -0.0194   0.0137   1.0000
  15.500   1.2918   0.08221   0.07684  -0.0200   0.0131   1.0000
  15.750   1.2882   0.08584   0.08053  -0.0208   0.0127   1.0000
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