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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 200,000
Max Cl/Cd: 61.47 at α=11.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w153-il-200000-n5.txt
Download as CSV file: xf-fx77w153-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3865   0.08469   0.07956  -0.0140   0.4758   0.0222
  -8.500  -0.3857   0.08051   0.07538  -0.0170   0.4730   0.0220
  -8.250  -0.3887   0.07511   0.07000  -0.0223   0.4707   0.0217
  -8.000  -0.3974   0.06927   0.06411  -0.0272   0.4690   0.0214
  -7.750  -0.4030   0.06292   0.05764  -0.0311   0.4672   0.0210
  -7.500  -0.4083   0.05613   0.05063  -0.0336   0.4655   0.0206
  -7.250  -0.4137   0.04867   0.04280  -0.0345   0.4641   0.0201
  -7.000  -0.4210   0.04008   0.03356  -0.0335   0.4629   0.0196
  -6.750  -0.4154   0.03481   0.02765  -0.0319   0.4607   0.0195
  -6.500  -0.4007   0.03174   0.02410  -0.0305   0.4582   0.0196
  -6.250  -0.3821   0.02943   0.02140  -0.0294   0.4552   0.0197
  -6.000  -0.3613   0.02753   0.01916  -0.0284   0.4521   0.0200
  -5.750  -0.3390   0.02591   0.01720  -0.0276   0.4490   0.0204
  -5.500  -0.3154   0.02448   0.01545  -0.0268   0.4461   0.0209
  -5.250  -0.2910   0.02321   0.01385  -0.0260   0.4435   0.0215
  -5.000  -0.2657   0.02209   0.01242  -0.0254   0.4412   0.0222
  -4.750  -0.2400   0.02129   0.01152  -0.0249   0.4389   0.0228
  -4.500  -0.2140   0.02067   0.01084  -0.0245   0.4366   0.0236
  -4.250  -0.1878   0.02004   0.01009  -0.0241   0.4345   0.0248
  -4.000  -0.1613   0.01948   0.00935  -0.0236   0.4326   0.0268
  -3.750  -0.1356   0.01897   0.00886  -0.0233   0.4308   0.0287
  -3.500  -0.1092   0.01852   0.00827  -0.0228   0.4291   0.0314
  -3.250  -0.0835   0.01807   0.00782  -0.0224   0.4276   0.0337
  -3.000  -0.0571   0.01776   0.00742  -0.0220   0.4262   0.0363
  -2.750  -0.0304   0.01751   0.00715  -0.0217   0.4248   0.0387
  -2.500  -0.0033   0.01733   0.00693  -0.0215   0.4234   0.0418
  -2.250   0.0238   0.01714   0.00674  -0.0213   0.4220   0.0453
  -2.000   0.0511   0.01702   0.00656  -0.0211   0.4206   0.0493
  -1.750   0.0777   0.01678   0.00633  -0.0208   0.4188   0.0535
  -1.500   0.1048   0.01662   0.00611  -0.0205   0.4167   0.0572
  -1.250   0.1316   0.01642   0.00589  -0.0202   0.4147   0.0609
  -1.000   0.1586   0.01626   0.00572  -0.0200   0.4129   0.0673
  -0.750   0.1855   0.01613   0.00559  -0.0197   0.4113   0.0855
  -0.500   0.2116   0.01591   0.00550  -0.0194   0.4101   0.1326
  -0.250   0.2368   0.01558   0.00547  -0.0190   0.4090   0.2257
   0.000   0.2593   0.01498   0.00548  -0.0183   0.4079   0.3898
   0.250   0.2777   0.01421   0.00552  -0.0165   0.4068   0.6056
   0.750   0.4036   0.01412   0.00625  -0.0293   0.4034   0.9670
   1.000   0.4610   0.01435   0.00638  -0.0353   0.4017   0.9893
   1.250   0.5165   0.01446   0.00639  -0.0411   0.4000   1.0000
   1.500   0.5421   0.01458   0.00643  -0.0407   0.3984   1.0000
   1.750   0.5677   0.01470   0.00647  -0.0403   0.3968   1.0000
   2.000   0.5933   0.01484   0.00652  -0.0400   0.3953   1.0000
   2.250   0.6189   0.01502   0.00661  -0.0396   0.3939   1.0000
   2.500   0.6444   0.01520   0.00675  -0.0393   0.3924   1.0000
   2.750   0.6698   0.01535   0.00692  -0.0389   0.3905   1.0000
   3.000   0.6951   0.01552   0.00709  -0.0385   0.3886   1.0000
   3.250   0.7204   0.01569   0.00727  -0.0381   0.3866   1.0000
   3.500   0.7457   0.01586   0.00743  -0.0377   0.3847   1.0000
   3.750   0.7709   0.01603   0.00757  -0.0374   0.3829   1.0000
   4.000   0.7962   0.01620   0.00771  -0.0369   0.3812   1.0000
   4.250   0.8215   0.01637   0.00785  -0.0366   0.3797   1.0000
   4.500   0.8468   0.01657   0.00800  -0.0362   0.3782   1.0000
   4.750   0.8717   0.01680   0.00824  -0.0357   0.3764   1.0000
   5.000   0.8960   0.01703   0.00855  -0.0353   0.3741   1.0000
   5.250   0.9204   0.01725   0.00881  -0.0348   0.3717   1.0000
   5.500   0.9449   0.01745   0.00905  -0.0343   0.3694   1.0000
   5.750   0.9695   0.01764   0.00925  -0.0339   0.3674   1.0000
   6.000   0.9943   0.01783   0.00944  -0.0334   0.3655   1.0000
   6.250   1.0191   0.01801   0.00961  -0.0330   0.3638   1.0000
   6.500   1.0441   0.01821   0.00978  -0.0326   0.3621   1.0000
   6.750   1.0670   0.01852   0.01019  -0.0320   0.3595   1.0000
   7.000   1.0899   0.01880   0.01057  -0.0314   0.3566   1.0000
   7.250   1.1132   0.01905   0.01090  -0.0308   0.3540   1.0000
   7.500   1.1369   0.01927   0.01116  -0.0302   0.3517   1.0000
   7.750   1.1607   0.01948   0.01139  -0.0297   0.3496   1.0000
   8.000   1.1848   0.01968   0.01159  -0.0292   0.3477   1.0000
   8.250   1.2090   0.01993   0.01184  -0.0287   0.3458   1.0000
   8.500   1.2289   0.02036   0.01247  -0.0278   0.3427   1.0000
   8.750   1.2498   0.02074   0.01297  -0.0270   0.3396   1.0000
   9.000   1.2715   0.02104   0.01337  -0.0263   0.3367   1.0000
   9.250   1.2937   0.02128   0.01366  -0.0256   0.3342   1.0000
   9.500   1.3164   0.02148   0.01389  -0.0249   0.3320   1.0000
   9.750   1.3371   0.02182   0.01432  -0.0241   0.3292   1.0000
  10.000   1.3540   0.02235   0.01506  -0.0228   0.3248   1.0000
  10.250   1.3732   0.02266   0.01548  -0.0218   0.3207   1.0000
  10.500   1.3943   0.02273   0.01560  -0.0210   0.3169   1.0000
  10.750   1.4105   0.02318   0.01622  -0.0197   0.3107   1.0000
  11.000   1.4293   0.02331   0.01641  -0.0187   0.3048   1.0000
  11.250   1.4470   0.02354   0.01669  -0.0175   0.2993   1.0000
  11.500   1.4628   0.02391   0.01711  -0.0162   0.2937   1.0000
  11.750   1.4785   0.02420   0.01741  -0.0149   0.2892   1.0000
  12.000   1.4891   0.02485   0.01814  -0.0131   0.2843   1.0000
  12.250   1.4946   0.02569   0.01906  -0.0108   0.2787   1.0000
  12.500   1.5004   0.02657   0.01993  -0.0089   0.2734   1.0000
  12.750   1.5019   0.02808   0.02158  -0.0074   0.2674   1.0000
  13.000   1.5011   0.03002   0.02362  -0.0066   0.2608   1.0000
  13.250   1.4986   0.03243   0.02611  -0.0063   0.2547   1.0000
  13.500   1.4909   0.03575   0.02953  -0.0067   0.2482   1.0000
  13.750   1.4838   0.03908   0.03288  -0.0072   0.2423   1.0000
  14.000   1.4702   0.04339   0.03731  -0.0081   0.2370   1.0000
  14.250   1.4584   0.04739   0.04136  -0.0087   0.2319   1.0000
  14.500   1.4531   0.05051   0.04447  -0.0089   0.2273   1.0000
  14.750   1.4328   0.05571   0.04984  -0.0099   0.2229   1.0000
  15.000   1.4160   0.06042   0.05464  -0.0107   0.2179   1.0000
  15.250   1.4110   0.06360   0.05782  -0.0110   0.2130   1.0000
  15.500   1.3921   0.06893   0.06330  -0.0122   0.2083   1.0000
  15.750   1.3754   0.07406   0.06854  -0.0134   0.2028   1.0000
  16.000   1.3725   0.07732   0.07182  -0.0140   0.1972   1.0000
  16.250   1.3568   0.08249   0.07710  -0.0153   0.1917   1.0000
  16.500   1.3529   0.08598   0.08061  -0.0161   0.1857   1.0000
  16.750   1.3456   0.09006   0.08473  -0.0171   0.1798   1.0000
  17.000   1.3367   0.09439   0.08912  -0.0182   0.1733   1.0000
  17.250   1.3320   0.09813   0.09287  -0.0192   0.1670   1.0000
  17.500   1.3157   0.10379   0.09868  -0.0208   0.1603   1.0000
  17.750   1.3068   0.10832   0.10325  -0.0222   0.1526   1.0000
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