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FX 77-W-121 (fx77w121-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 77-W-121 (fx77w121-il)
Reynolds number: 200,000
Max Cl/Cd: 73.62 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w121-il-200000-n5.txt
Download as CSV file: xf-fx77w121-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2272   0.09120   0.08650  -0.0236   0.5252   0.0243
  -9.250  -0.2250   0.08746   0.08274  -0.0248   0.5235   0.0243
  -9.000  -0.2229   0.08361   0.07889  -0.0261   0.5217   0.0243
  -8.750  -0.2215   0.07970   0.07500  -0.0274   0.5198   0.0243
  -8.250  -0.2863   0.08321   0.07819  -0.0328   0.5226   0.0176
  -8.000  -0.2854   0.07998   0.07499  -0.0339   0.5203   0.0174
  -7.750  -0.2861   0.07683   0.07187  -0.0349   0.5183   0.0171
  -7.500  -0.2869   0.07413   0.06917  -0.0354   0.5163   0.0165
  -7.250  -0.2922   0.06960   0.06463  -0.0379   0.5149   0.0169
  -7.000  -0.2895   0.06599   0.06098  -0.0394   0.5130   0.0164
  -6.750  -0.2852   0.06213   0.05704  -0.0409   0.5114   0.0161
  -6.500  -0.2805   0.05745   0.05223  -0.0425   0.5100   0.0164
  -6.250  -0.2747   0.05045   0.04493  -0.0440   0.5090   0.0177
  -6.000  -0.2651   0.04680   0.04111  -0.0436   0.5072   0.0175
  -5.750  -0.2546   0.04297   0.03705  -0.0429   0.5053   0.0173
  -5.500  -0.2440   0.03861   0.03237  -0.0415   0.5035   0.0172
  -5.250  -0.2320   0.03448   0.02784  -0.0398   0.5017   0.0172
  -5.000  -0.2185   0.03067   0.02355  -0.0376   0.5001   0.0173
  -4.750  -0.2024   0.02743   0.01974  -0.0355   0.4985   0.0175
  -4.500  -0.1836   0.02487   0.01663  -0.0337   0.4970   0.0180
  -4.250  -0.1621   0.02336   0.01485  -0.0326   0.4955   0.0187
  -4.000  -0.1382   0.02286   0.01421  -0.0320   0.4940   0.0201
  -3.750  -0.1137   0.02188   0.01300  -0.0312   0.4924   0.0216
  -3.500  -0.0885   0.02070   0.01151  -0.0304   0.4906   0.0232
  -3.250  -0.0625   0.01967   0.01021  -0.0296   0.4886   0.0241
  -3.000  -0.0373   0.01848   0.00889  -0.0290   0.4868   0.0257
  -2.750  -0.0114   0.01810   0.00846  -0.0286   0.4851   0.0285
  -2.500   0.0147   0.01755   0.00780  -0.0281   0.4836   0.0309
  -2.250   0.0407   0.01701   0.00713  -0.0275   0.4823   0.0327
  -2.000   0.0655   0.01641   0.00648  -0.0269   0.4811   0.0360
  -1.750   0.0910   0.01610   0.00613  -0.0263   0.4799   0.0398
  -1.250   0.1417   0.01549   0.00541  -0.0251   0.4771   0.0476
  -1.000   0.1675   0.01530   0.00520  -0.0246   0.4754   0.0554
  -0.750   0.1930   0.01507   0.00498  -0.0241   0.4738   0.0666
  -0.500   0.2180   0.01480   0.00485  -0.0235   0.4725   0.1046
  -0.250   0.2402   0.01422   0.00478  -0.0226   0.4712   0.2545
   0.000   0.2555   0.01322   0.00474  -0.0204   0.4700   0.5422
   0.500   0.4649   0.01273   0.00486  -0.0525   0.4659   1.0000
   0.750   0.4901   0.01286   0.00487  -0.0520   0.4647   1.0000
   1.000   0.5153   0.01299   0.00494  -0.0515   0.4634   1.0000
   1.250   0.5404   0.01313   0.00505  -0.0511   0.4621   1.0000
   1.500   0.5656   0.01327   0.00518  -0.0506   0.4607   1.0000
   1.750   0.5907   0.01343   0.00531  -0.0501   0.4593   1.0000
   2.000   0.6158   0.01359   0.00544  -0.0497   0.4578   1.0000
   2.250   0.6410   0.01374   0.00556  -0.0492   0.4561   1.0000
   2.500   0.6662   0.01389   0.00569  -0.0488   0.4545   1.0000
   2.750   0.6914   0.01406   0.00583  -0.0484   0.4532   1.0000
   3.000   0.7167   0.01422   0.00596  -0.0479   0.4518   1.0000
   3.250   0.7421   0.01439   0.00607  -0.0475   0.4502   1.0000
   3.500   0.7670   0.01459   0.00629  -0.0471   0.4485   1.0000
   3.750   0.7916   0.01480   0.00658  -0.0466   0.4465   1.0000
   4.000   0.8162   0.01502   0.00686  -0.0461   0.4446   1.0000
   4.250   0.8409   0.01522   0.00709  -0.0457   0.4424   1.0000
   4.500   0.8657   0.01541   0.00731  -0.0452   0.4405   1.0000
   4.750   0.8908   0.01556   0.00749  -0.0448   0.4383   1.0000
   5.000   0.9160   0.01571   0.00762  -0.0444   0.4364   1.0000
   5.250   0.9411   0.01589   0.00780  -0.0439   0.4342   1.0000
   5.500   0.9644   0.01614   0.00820  -0.0434   0.4312   1.0000
   5.750   0.9884   0.01637   0.00854  -0.0428   0.4284   1.0000
   6.000   1.0127   0.01654   0.00878  -0.0423   0.4256   1.0000
   6.250   1.0376   0.01665   0.00893  -0.0419   0.4230   1.0000
   6.500   1.0629   0.01677   0.00907  -0.0415   0.4208   1.0000
   6.750   1.0860   0.01702   0.00946  -0.0408   0.4176   1.0000
   7.000   1.1089   0.01729   0.00988  -0.0402   0.4140   1.0000
   7.250   1.1326   0.01750   0.01021  -0.0396   0.4111   1.0000
   7.500   1.1568   0.01767   0.01045  -0.0391   0.4085   1.0000
   7.750   1.1816   0.01779   0.01064  -0.0387   0.4061   1.0000
   8.000   1.2036   0.01808   0.01112  -0.0379   0.4021   1.0000
   8.250   1.2256   0.01834   0.01157  -0.0372   0.3977   1.0000
   8.500   1.2491   0.01849   0.01184  -0.0366   0.3942   1.0000
   8.750   1.2734   0.01854   0.01199  -0.0360   0.3911   1.0000
   9.000   1.2931   0.01877   0.01248  -0.0350   0.3824   1.0000
   9.250   1.3152   0.01848   0.01232  -0.0340   0.3672   1.0000
   9.500   1.3365   0.01825   0.01211  -0.0329   0.3453   1.0000
   9.750   1.3532   0.01838   0.01211  -0.0313   0.3120   1.0000
  10.000   1.3601   0.01930   0.01279  -0.0287   0.2722   1.0000
  10.250   1.3561   0.02099   0.01421  -0.0251   0.2304   1.0000
  10.500   1.3431   0.02317   0.01618  -0.0210   0.1937   1.0000
  10.750   1.3277   0.02525   0.01820  -0.0169   0.1737   1.0000
  11.000   1.3089   0.02874   0.02165  -0.0155   0.1523   1.0000
  11.250   1.2868   0.03355   0.02636  -0.0157   0.1276   1.0000
  11.500   1.2701   0.03795   0.03070  -0.0159   0.1082   1.0000
  11.750   1.2522   0.04244   0.03511  -0.0160   0.0905   1.0000
  12.000   1.2270   0.04767   0.04016  -0.0161   0.0626   1.0000
  12.250   1.2151   0.05154   0.04397  -0.0161   0.0492   1.0000
  12.500   1.2046   0.05530   0.04770  -0.0162   0.0372   1.0000
  12.750   1.1907   0.05953   0.05185  -0.0163   0.0261   1.0000
  13.000   1.1824   0.06337   0.05570  -0.0166   0.0204   1.0000
  13.250   1.1780   0.06686   0.05926  -0.0170   0.0180   1.0000
  13.500   1.1764   0.07008   0.06259  -0.0173   0.0161   1.0000
  13.750   1.1737   0.07350   0.06608  -0.0177   0.0148   1.0000
  14.000   1.1663   0.07765   0.07031  -0.0184   0.0133   1.0000
  14.250   1.1630   0.08129   0.07405  -0.0190   0.0129   1.0000
  14.500   1.1612   0.08480   0.07770  -0.0196   0.0121   1.0000
  14.750   1.1591   0.08841   0.08143  -0.0203   0.0120   1.0000
  15.000   1.1549   0.09236   0.08549  -0.0210   0.0113   1.0000
  15.250   1.1520   0.09617   0.08939  -0.0219   0.0109   1.0000
  15.500   1.1487   0.10008   0.09343  -0.0227   0.0102   1.0000
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