Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 76-MP-140 (fx76mp140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 76-MP-140 (fx76mp140-il)
Reynolds number: 1,000,000
Max Cl/Cd: 153.4 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx76mp140-il-1000000-n5.txt
Download as CSV file: xf-fx76mp140-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 76-MP-140                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5178   0.02826   0.02447  -0.1890   0.7720   0.0136
 -13.500  -0.5193   0.02496   0.02100  -0.1918   0.7702   0.0137
 -13.250  -0.5082   0.02325   0.01917  -0.1925   0.7686   0.0139
 -13.000  -0.4925   0.02199   0.01781  -0.1927   0.7670   0.0142
 -12.750  -0.4742   0.02098   0.01670  -0.1928   0.7654   0.0146
 -12.500  -0.4550   0.02002   0.01564  -0.1929   0.7637   0.0148
 -12.250  -0.4339   0.01926   0.01477  -0.1929   0.7621   0.0152
 -12.000  -0.4123   0.01852   0.01393  -0.1928   0.7604   0.0155
 -11.750  -0.3897   0.01786   0.01316  -0.1928   0.7586   0.0158
 -11.500  -0.3663   0.01727   0.01245  -0.1928   0.7567   0.0159
 -11.250  -0.3430   0.01658   0.01168  -0.1928   0.7555   0.0163
 -11.000  -0.3191   0.01593   0.01097  -0.1929   0.7544   0.0166
 -10.750  -0.2942   0.01540   0.01039  -0.1929   0.7531   0.0170
 -10.500  -0.2685   0.01499   0.00994  -0.1930   0.7517   0.0175
 -10.250  -0.2428   0.01454   0.00942  -0.1930   0.7504   0.0178
 -10.000  -0.2168   0.01414   0.00896  -0.1931   0.7489   0.0182
  -9.750  -0.1905   0.01375   0.00850  -0.1932   0.7474   0.0186
  -9.500  -0.1641   0.01340   0.00807  -0.1932   0.7457   0.0190
  -9.250  -0.1375   0.01306   0.00766  -0.1933   0.7440   0.0193
  -9.000  -0.1112   0.01263   0.00718  -0.1933   0.7425   0.0200
  -8.750  -0.0843   0.01231   0.00681  -0.1934   0.7409   0.0205
  -8.500  -0.0570   0.01206   0.00651  -0.1935   0.7393   0.0211
  -8.250  -0.0297   0.01176   0.00618  -0.1936   0.7381   0.0216
  -8.000  -0.0023   0.01147   0.00585  -0.1937   0.7366   0.0220
  -7.750   0.0253   0.01119   0.00552  -0.1938   0.7350   0.0224
  -7.500   0.0529   0.01094   0.00523  -0.1939   0.7334   0.0228
  -7.250   0.0804   0.01064   0.00490  -0.1940   0.7316   0.0235
  -7.000   0.1081   0.01041   0.00464  -0.1941   0.7298   0.0242
  -6.750   0.1359   0.01021   0.00440  -0.1942   0.7281   0.0250
  -6.500   0.1637   0.01003   0.00419  -0.1943   0.7264   0.0258
  -6.250   0.1915   0.00986   0.00397  -0.1944   0.7246   0.0266
  -6.000   0.2195   0.00968   0.00376  -0.1945   0.7229   0.0276
  -5.750   0.2475   0.00951   0.00360  -0.1946   0.7214   0.0289
  -5.500   0.2757   0.00936   0.00344  -0.1947   0.7195   0.0303
  -5.250   0.3037   0.00921   0.00328  -0.1948   0.7171   0.0315
  -5.000   0.3315   0.00906   0.00313  -0.1949   0.7146   0.0332
  -4.750   0.3594   0.00895   0.00300  -0.1949   0.7123   0.0348
  -4.500   0.3873   0.00886   0.00287  -0.1949   0.7102   0.0362
  -4.250   0.4151   0.00874   0.00274  -0.1950   0.7080   0.0382
  -4.000   0.4432   0.00864   0.00264  -0.1951   0.7061   0.0401
  -3.750   0.4714   0.00855   0.00254  -0.1952   0.7040   0.0415
  -3.500   0.4992   0.00844   0.00244  -0.1952   0.7011   0.0436
  -3.250   0.5269   0.00834   0.00234  -0.1952   0.6981   0.0456
  -3.000   0.5545   0.00828   0.00226  -0.1952   0.6952   0.0475
  -2.750   0.5819   0.00821   0.00217  -0.1951   0.6926   0.0499
  -2.500   0.6098   0.00814   0.00212  -0.1952   0.6903   0.0533
  -2.250   0.6377   0.00807   0.00207  -0.1953   0.6876   0.0575
  -2.000   0.6653   0.00800   0.00202  -0.1953   0.6846   0.0619
  -1.750   0.6926   0.00795   0.00197  -0.1952   0.6811   0.0665
  -1.500   0.7194   0.00791   0.00193  -0.1950   0.6774   0.0722
  -1.250   0.7467   0.00787   0.00190  -0.1949   0.6739   0.0779
  -1.000   0.7741   0.00782   0.00188  -0.1949   0.6703   0.0855
  -0.750   0.8010   0.00778   0.00186  -0.1948   0.6665   0.0963
  -0.500   0.8274   0.00775   0.00186  -0.1945   0.6624   0.1089
  -0.250   0.8540   0.00773   0.00186  -0.1943   0.6583   0.1224
   0.000   0.8805   0.00770   0.00187  -0.1941   0.6530   0.1376
   0.250   0.9061   0.00770   0.00188  -0.1938   0.6476   0.1543
   0.500   0.9319   0.00769   0.00191  -0.1934   0.6426   0.1738
   0.750   0.9580   0.00766   0.00195  -0.1932   0.6378   0.2044
   1.000   0.9829   0.00761   0.00200  -0.1927   0.6325   0.2506
   1.250   1.0074   0.00758   0.00206  -0.1921   0.6269   0.2996
   1.500   1.0323   0.00753   0.00213  -0.1917   0.6208   0.3577
   1.750   1.0552   0.00749   0.00222  -0.1908   0.6143   0.4275
   2.000   1.0777   0.00732   0.00234  -0.1900   0.6077   0.5640
   2.250   1.0968   0.00723   0.00251  -0.1883   0.5983   0.6941
   2.500   1.1183   0.00729   0.00265  -0.1870   0.5886   0.7449
   2.750   1.1388   0.00743   0.00278  -0.1855   0.5793   0.7695
   3.250   1.1789   0.00770   0.00305  -0.1824   0.5601   0.8077
   3.500   1.1946   0.00785   0.00320  -0.1800   0.5503   0.8271
   3.750   1.2117   0.00798   0.00335  -0.1778   0.5404   0.8487
   4.000   1.2261   0.00816   0.00356  -0.1751   0.5292   0.8801
   4.250   1.2447   0.00837   0.00380  -0.1734   0.5160   0.9180
   4.500   1.2946   0.00871   0.00411  -0.1789   0.4996   0.9573
   4.750   1.3176   0.00909   0.00441  -0.1784   0.4833   1.0000
   5.000   1.3386   0.00944   0.00470  -0.1774   0.4700   1.0000
   5.250   1.3599   0.00981   0.00501  -0.1766   0.4569   1.0000
   5.500   1.3803   0.01025   0.00539  -0.1756   0.4427   1.0000
   5.750   1.3998   0.01076   0.00582  -0.1746   0.4272   1.0000
   6.000   1.4198   0.01127   0.00627  -0.1737   0.4141   1.0000
   6.250   1.4387   0.01183   0.00678  -0.1728   0.4011   1.0000
   6.500   1.4591   0.01232   0.00724  -0.1720   0.3908   1.0000
   6.750   1.4782   0.01289   0.00777  -0.1711   0.3814   1.0000
   7.000   1.4964   0.01350   0.00835  -0.1701   0.3717   1.0000
   7.250   1.5148   0.01411   0.00895  -0.1692   0.3622   1.0000
   7.500   1.5307   0.01487   0.00967  -0.1679   0.3514   1.0000
   8.000   1.5590   0.01664   0.01134  -0.1651   0.3248   1.0000
   8.250   1.5726   0.01757   0.01222  -0.1636   0.3121   1.0000
   8.500   1.5858   0.01852   0.01314  -0.1622   0.3009   1.0000
   8.750   1.5975   0.01958   0.01415  -0.1606   0.2882   1.0000
   9.000   1.6119   0.02046   0.01502  -0.1593   0.2783   1.0000
   9.250   1.6217   0.02165   0.01615  -0.1575   0.2645   1.0000
   9.500   1.6315   0.02284   0.01728  -0.1557   0.2509   1.0000
   9.750   1.6393   0.02416   0.01855  -0.1537   0.2363   1.0000
  10.000   1.6473   0.02547   0.01980  -0.1518   0.2225   1.0000
  10.250   1.6536   0.02693   0.02119  -0.1497   0.2076   1.0000
  10.500   1.6586   0.02849   0.02266  -0.1475   0.1909   1.0000
  10.750   1.6628   0.03015   0.02424  -0.1454   0.1749   1.0000
  11.000   1.6712   0.03154   0.02560  -0.1437   0.1651   1.0000
  11.250   1.6782   0.03307   0.02709  -0.1419   0.1554   1.0000
  11.500   1.6886   0.03434   0.02837  -0.1405   0.1482   1.0000
  11.750   1.6950   0.03595   0.02995  -0.1388   0.1391   1.0000
  12.000   1.7034   0.03744   0.03142  -0.1374   0.1307   1.0000
  12.250   1.7073   0.03932   0.03324  -0.1355   0.1183   1.0000
  12.500   1.7137   0.04103   0.03493  -0.1340   0.1108   1.0000
  12.750   1.7177   0.04293   0.03679  -0.1323   0.1009   1.0000
  13.000   1.7233   0.04477   0.03862  -0.1308   0.0925   1.0000
  13.250   1.7244   0.04701   0.04081  -0.1290   0.0803   1.0000
  13.500   1.7206   0.04979   0.04351  -0.1270   0.0651   1.0000
  13.750   1.7125   0.05300   0.04663  -0.1248   0.0483   1.0000
  14.000   1.7126   0.05550   0.04911  -0.1232   0.0407   1.0000
  14.250   1.7148   0.05789   0.05151  -0.1219   0.0363   1.0000
  14.500   1.7168   0.06029   0.05392  -0.1207   0.0314   1.0000
  14.750   1.7196   0.06266   0.05633  -0.1196   0.0282   1.0000
  15.000   1.7225   0.06500   0.05870  -0.1185   0.0255   1.0000
  15.250   1.7245   0.06752   0.06125  -0.1175   0.0235   1.0000
  15.500   1.7274   0.06993   0.06370  -0.1166   0.0218   1.0000
  15.750   1.7305   0.07239   0.06622  -0.1158   0.0208   1.0000
  16.000   1.7332   0.07488   0.06875  -0.1150   0.0198   1.0000
  16.250   1.7337   0.07766   0.07159  -0.1142   0.0187   1.0000
  16.500   1.7365   0.08016   0.07415  -0.1135   0.0181   1.0000
  16.750   1.7383   0.08282   0.07688  -0.1129   0.0173   1.0000
  17.000   1.7391   0.08563   0.07974  -0.1124   0.0165   1.0000
  17.250   1.7389   0.08857   0.08275  -0.1118   0.0157   1.0000
  17.500   1.7383   0.09161   0.08585  -0.1114   0.0150   1.0000
  17.750   1.7395   0.09440   0.08871  -0.1111   0.0142   1.0000
  18.000   1.7378   0.09758   0.09195  -0.1108   0.0133   1.0000
  18.250   1.7354   0.10085   0.09528  -0.1105   0.0125   1.0000
  18.500   1.7343   0.10399   0.09848  -0.1104   0.0119   1.0000
  18.750   1.7319   0.10734   0.10190  -0.1104   0.0111   1.0000
  19.000   1.7294   0.11069   0.10531  -0.1104   0.0103   1.0000
  19.250   1.7259   0.11423   0.10891  -0.1106   0.0098   1.0000
<< Back to FX 76-MP-140 (fx76mp140-il)

Polar data table (+)

Polar graphs


<< Back to FX 76-MP-140 (fx76mp140-il)