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-160 (fx76mp160-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 76-MP-160 (fx76mp160-il)
Reynolds number: 1,000,000
Max Cl/Cd: 152.53 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76mp160-il-1000000.txt
Download as CSV file: xf-fx76mp160-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 76-MP-160                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.4663   0.08011   0.07687  -0.1259   0.8261   0.0221
 -15.750  -0.4946   0.07050   0.06710  -0.1342   0.8242   0.0220
 -15.500  -0.5166   0.06155   0.05798  -0.1437   0.8221   0.0220
 -15.250  -0.5270   0.05485   0.05116  -0.1510   0.8202   0.0219
 -15.000  -0.5367   0.04870   0.04490  -0.1574   0.8186   0.0219
 -14.750  -0.5428   0.04274   0.03880  -0.1643   0.8166   0.0218
 -14.500  -0.5518   0.03587   0.03173  -0.1728   0.8143   0.0219
 -14.250  -0.5509   0.03111   0.02682  -0.1792   0.8119   0.0220
 -14.000  -0.5439   0.02806   0.02363  -0.1833   0.8095   0.0221
 -13.750  -0.5359   0.02576   0.02121  -0.1857   0.8070   0.0220
 -13.500  -0.5334   0.02342   0.01873  -0.1874   0.8040   0.0223
 -13.250  -0.5287   0.02189   0.01711  -0.1873   0.8017   0.0224
 -13.000  -0.5254   0.02085   0.01601  -0.1857   0.8002   0.0223
 -12.750  -0.5225   0.01987   0.01496  -0.1838   0.7985   0.0224
 -12.500  -0.5099   0.01908   0.01412  -0.1827   0.7967   0.0228
 -12.250  -0.4943   0.01838   0.01337  -0.1818   0.7950   0.0232
 -12.000  -0.4768   0.01771   0.01264  -0.1811   0.7933   0.0233
 -11.750  -0.4575   0.01712   0.01198  -0.1805   0.7917   0.0235
 -11.500  -0.4368   0.01658   0.01139  -0.1800   0.7901   0.0238
 -11.250  -0.4154   0.01606   0.01080  -0.1795   0.7885   0.0240
 -11.000  -0.3928   0.01559   0.01026  -0.1792   0.7867   0.0241
 -10.750  -0.3692   0.01516   0.00975  -0.1790   0.7845   0.0243
 -10.500  -0.3454   0.01474   0.00929  -0.1787   0.7829   0.0246
 -10.250  -0.3215   0.01431   0.00881  -0.1784   0.7819   0.0248
 -10.000  -0.2970   0.01391   0.00837  -0.1782   0.7807   0.0251
  -9.750  -0.2718   0.01355   0.00797  -0.1780   0.7794   0.0253
  -9.500  -0.2463   0.01319   0.00757  -0.1779   0.7781   0.0255
  -9.250  -0.2207   0.01281   0.00715  -0.1778   0.7767   0.0260
  -9.000  -0.1943   0.01250   0.00682  -0.1777   0.7752   0.0266
  -8.750  -0.1674   0.01224   0.00655  -0.1777   0.7736   0.0272
  -8.500  -0.1404   0.01198   0.00627  -0.1777   0.7718   0.0278
  -8.250  -0.1131   0.01176   0.00601  -0.1777   0.7700   0.0286
  -8.000  -0.0856   0.01155   0.00576  -0.1778   0.7680   0.0294
  -7.750  -0.0575   0.01139   0.00559  -0.1780   0.7658   0.0307
  -7.500  -0.0294   0.01127   0.00546  -0.1781   0.7640   0.0322
  -7.250  -0.0016   0.01114   0.00532  -0.1781   0.7630   0.0339
  -7.000   0.0255   0.01087   0.00505  -0.1781   0.7615   0.0355
  -6.750   0.0531   0.01069   0.00487  -0.1781   0.7598   0.0374
  -6.500   0.0813   0.01058   0.00472  -0.1782   0.7581   0.0389
  -6.250   0.1088   0.01031   0.00444  -0.1783   0.7562   0.0407
  -6.000   0.1368   0.01010   0.00422  -0.1784   0.7544   0.0424
  -5.750   0.1651   0.00995   0.00404  -0.1785   0.7526   0.0438
  -5.500   0.1933   0.00979   0.00385  -0.1786   0.7506   0.0451
  -5.250   0.2217   0.00964   0.00369  -0.1788   0.7483   0.0468
  -5.000   0.2508   0.00956   0.00360  -0.1791   0.7456   0.0487
  -4.750   0.2791   0.00945   0.00351  -0.1793   0.7441   0.0509
  -4.500   0.3071   0.00932   0.00342  -0.1793   0.7429   0.0536
  -4.000   0.3635   0.00910   0.00323  -0.1795   0.7394   0.0600
  -3.750   0.3919   0.00901   0.00314  -0.1795   0.7372   0.0631
  -3.500   0.4201   0.00885   0.00299  -0.1796   0.7345   0.0667
  -3.250   0.4485   0.00874   0.00286  -0.1797   0.7321   0.0698
  -3.000   0.4770   0.00862   0.00274  -0.1798   0.7296   0.0741
  -2.750   0.5058   0.00854   0.00267  -0.1801   0.7264   0.0818
  -2.500   0.5336   0.00842   0.00262  -0.1801   0.7241   0.0958
  -2.250   0.5612   0.00830   0.00254  -0.1800   0.7213   0.1042
  -2.000   0.5892   0.00820   0.00246  -0.1801   0.7183   0.1110
  -1.750   0.6170   0.00807   0.00240  -0.1801   0.7151   0.1242
  -1.500   0.6450   0.00799   0.00233  -0.1801   0.7117   0.1410
  -1.250   0.6733   0.00794   0.00227  -0.1802   0.7079   0.1499
  -1.000   0.7011   0.00788   0.00225  -0.1802   0.7051   0.1587
  -0.750   0.7286   0.00779   0.00225  -0.1802   0.7020   0.1765
  -0.500   0.7563   0.00774   0.00223  -0.1802   0.6985   0.1923
  -0.250   0.7837   0.00768   0.00218  -0.1801   0.6941   0.2015
   0.000   0.8107   0.00765   0.00215  -0.1799   0.6890   0.2150
   0.250   0.8377   0.00757   0.00216  -0.1798   0.6846   0.2423
   0.500   0.8649   0.00752   0.00217  -0.1797   0.6796   0.2608
   0.750   0.8916   0.00745   0.00218  -0.1795   0.6745   0.2953
   1.000   0.9176   0.00744   0.00218  -0.1792   0.6690   0.3174
   1.250   0.9445   0.00735   0.00222  -0.1791   0.6639   0.3621
   1.500   0.9705   0.00730   0.00225  -0.1788   0.6575   0.3948
   1.750   0.9949   0.00726   0.00229  -0.1782   0.6505   0.4481
   2.000   1.0203   0.00711   0.00237  -0.1779   0.6441   0.5319
   2.250   1.0434   0.00702   0.00247  -0.1770   0.6358   0.6327
   2.500   1.0662   0.00704   0.00261  -0.1760   0.6264   0.6967
   2.750   1.0880   0.00715   0.00274  -0.1747   0.6144   0.7220
   3.000   1.1104   0.00728   0.00284  -0.1736   0.6015   0.7381
   3.250   1.1302   0.00746   0.00297  -0.1720   0.5880   0.7467
   3.500   1.1472   0.00769   0.00313  -0.1698   0.5739   0.7558
   3.750   1.1654   0.00787   0.00329  -0.1679   0.5599   0.7644
   4.000   1.1796   0.00807   0.00345  -0.1651   0.5457   0.7711
   4.250   1.1915   0.00835   0.00367  -0.1619   0.5302   0.7769
   4.750   1.2165   0.00897   0.00418  -0.1560   0.5029   0.7908
   5.000   1.2292   0.00928   0.00445  -0.1531   0.4920   0.7974
   5.250   1.2402   0.00965   0.00476  -0.1500   0.4765   0.8037
   5.500   1.2524   0.00997   0.00507  -0.1472   0.4639   0.8090
   5.750   1.2616   0.01040   0.00546  -0.1439   0.4519   0.8158
   6.000   1.2715   0.01085   0.00588  -0.1408   0.4402   0.8211
   6.250   1.2831   0.01127   0.00630  -0.1381   0.4298   0.8276
   6.500   1.2897   0.01190   0.00687  -0.1347   0.4140   0.8355
   6.750   1.2986   0.01251   0.00743  -0.1318   0.3990   0.8432
   7.000   1.3086   0.01311   0.00801  -0.1291   0.3875   0.8509
   7.250   1.3156   0.01387   0.00872  -0.1261   0.3749   0.8581
   7.500   1.3314   0.01433   0.00921  -0.1245   0.3668   0.8639
   7.750   1.3405   0.01508   0.00993  -0.1219   0.3538   0.8711
   8.000   1.3548   0.01564   0.01051  -0.1202   0.3436   0.8829
   8.250   1.3669   0.01636   0.01121  -0.1183   0.3329   0.8990
   8.500   1.3964   0.01703   0.01194  -0.1200   0.3236   0.9317
   8.750   1.4478   0.01786   0.01277  -0.1264   0.3124   0.9479
   9.000   1.4656   0.01856   0.01346  -0.1256   0.3048   1.0000
   9.250   1.4806   0.01948   0.01434  -0.1245   0.2960   1.0000
   9.500   1.5005   0.02010   0.01497  -0.1241   0.2892   1.0000
   9.750   1.5149   0.02106   0.01587  -0.1230   0.2779   1.0000
  10.000   1.5312   0.02191   0.01670  -0.1221   0.2709   1.0000
  10.250   1.5452   0.02288   0.01764  -0.1210   0.2635   1.0000
  10.500   1.5612   0.02373   0.01849  -0.1202   0.2573   1.0000
  10.750   1.5779   0.02455   0.01932  -0.1194   0.2515   1.0000
  11.000   1.5907   0.02563   0.02038  -0.1182   0.2442   1.0000
  11.250   1.6057   0.02654   0.02129  -0.1173   0.2372   1.0000
  11.500   1.6205   0.02748   0.02221  -0.1163   0.2283   1.0000
  11.750   1.6307   0.02875   0.02344  -0.1150   0.2194   1.0000
  12.000   1.6435   0.02984   0.02452  -0.1139   0.2130   1.0000
  12.250   1.6548   0.03103   0.02568  -0.1126   0.2064   1.0000
  12.500   1.6685   0.03207   0.02675  -0.1117   0.2013   1.0000
  12.750   1.6785   0.03337   0.02804  -0.1104   0.1932   1.0000
  13.000   1.6879   0.03474   0.02938  -0.1091   0.1862   1.0000
  13.250   1.7031   0.03568   0.03036  -0.1083   0.1816   1.0000
  13.500   1.7110   0.03720   0.03186  -0.1070   0.1724   1.0000
  13.750   1.7187   0.03872   0.03335  -0.1056   0.1645   1.0000
  14.000   1.7256   0.04031   0.03491  -0.1043   0.1575   1.0000
  14.250   1.7333   0.04191   0.03652  -0.1030   0.1517   1.0000
  14.500   1.7423   0.04338   0.03801  -0.1019   0.1456   1.0000
  14.750   1.7475   0.04517   0.03978  -0.1006   0.1389   1.0000
  15.000   1.7555   0.04679   0.04143  -0.0995   0.1337   1.0000
  15.250   1.7604   0.04863   0.04326  -0.0982   0.1258   1.0000
  15.500   1.7627   0.05077   0.04537  -0.0969   0.1188   1.0000
  15.750   1.7661   0.05282   0.04742  -0.0956   0.1142   1.0000
  16.000   1.7681   0.05502   0.04962  -0.0944   0.1083   1.0000
  16.250   1.7739   0.05692   0.05157  -0.0935   0.1051   1.0000
  16.500   1.7770   0.05902   0.05369  -0.0923   0.1004   1.0000
  16.750   1.7750   0.06168   0.05636  -0.0911   0.0951   1.0000
  17.000   1.7800   0.06366   0.05839  -0.0902   0.0913   1.0000
  17.250   1.7788   0.06630   0.06103  -0.0892   0.0856   1.0000
  17.500   1.7763   0.06906   0.06380  -0.0881   0.0808   1.0000
  17.750   1.7738   0.07187   0.06663  -0.0872   0.0775   1.0000
  18.000   1.7706   0.07474   0.06952  -0.0862   0.0740   1.0000
  18.250   1.7684   0.07761   0.07245  -0.0855   0.0713   1.0000
  18.500   1.7696   0.08010   0.07500  -0.0849   0.0690   1.0000
  18.750   1.7659   0.08320   0.07814  -0.0843   0.0662   1.0000
  19.000   1.7596   0.08656   0.08154  -0.0837   0.0629   1.0000
<< Back to FX 76-MP-160 (fx76mp160-il)

Polar data table (+)

Polar graphs


<< Back to FX 76-MP-160 (fx76mp160-il)