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=500,000 Ncrit=9


Details Polar file
Airfoil: FX 76-MP-160 (fx76mp160-il)
Reynolds number: 500,000
Max Cl/Cd: 120.92 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76mp160-il-500000.txt
Download as CSV file: xf-fx76mp160-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3257   0.03327   0.02870  -0.1915   0.8366   0.0308
 -12.250  -0.3312   0.03101   0.02632  -0.1918   0.8336   0.0310
 -12.000  -0.3378   0.02899   0.02417  -0.1909   0.8305   0.0311
 -11.750  -0.3434   0.02753   0.02259  -0.1889   0.8276   0.0312
 -11.500  -0.3445   0.02636   0.02129  -0.1869   0.8250   0.0313
 -11.250  -0.3366   0.02527   0.02005  -0.1856   0.8227   0.0316
 -11.000  -0.3258   0.02427   0.01892  -0.1845   0.8204   0.0317
 -10.750  -0.3134   0.02334   0.01789  -0.1833   0.8187   0.0320
 -10.500  -0.2987   0.02248   0.01693  -0.1822   0.8166   0.0323
 -10.250  -0.2820   0.02165   0.01598  -0.1812   0.8143   0.0326
 -10.000  -0.2633   0.02092   0.01513  -0.1805   0.8122   0.0331
  -9.750  -0.2429   0.02025   0.01435  -0.1799   0.8104   0.0335
  -9.500  -0.2212   0.01964   0.01362  -0.1795   0.8086   0.0338
  -9.250  -0.1991   0.01897   0.01285  -0.1791   0.8069   0.0342
  -9.000  -0.1772   0.01819   0.01203  -0.1788   0.8052   0.0348
  -8.750  -0.1535   0.01772   0.01153  -0.1786   0.8035   0.0355
  -8.500  -0.1303   0.01734   0.01112  -0.1782   0.8017   0.0362
  -8.250  -0.1070   0.01688   0.01062  -0.1778   0.8002   0.0372
  -8.000  -0.0834   0.01645   0.01013  -0.1773   0.7982   0.0382
  -7.750  -0.0599   0.01592   0.00955  -0.1769   0.7960   0.0395
  -7.500  -0.0362   0.01534   0.00900  -0.1766   0.7938   0.0412
  -7.250  -0.0106   0.01495   0.00856  -0.1765   0.7919   0.0437
  -7.000   0.0151   0.01447   0.00807  -0.1764   0.7899   0.0464
  -6.750   0.0429   0.01422   0.00778  -0.1766   0.7880   0.0494
  -6.500   0.0712   0.01401   0.00756  -0.1768   0.7861   0.0523
  -6.250   0.0998   0.01399   0.00748  -0.1770   0.7840   0.0550
  -6.000   0.1261   0.01386   0.00735  -0.1769   0.7822   0.0573
  -5.750   0.1524   0.01374   0.00724  -0.1767   0.7805   0.0597
  -5.500   0.1789   0.01362   0.00709  -0.1765   0.7785   0.0618
  -5.250   0.2055   0.01342   0.00688  -0.1764   0.7762   0.0636
  -5.000   0.2326   0.01315   0.00662  -0.1764   0.7736   0.0661
  -4.750   0.2609   0.01295   0.00639  -0.1765   0.7714   0.0688
  -4.500   0.2895   0.01270   0.00611  -0.1767   0.7693   0.0718
  -4.250   0.3186   0.01246   0.00587  -0.1771   0.7675   0.0760
  -4.000   0.3480   0.01231   0.00573  -0.1775   0.7654   0.0819
  -3.750   0.3749   0.01223   0.00570  -0.1774   0.7631   0.0906
  -3.500   0.4009   0.01209   0.00560  -0.1771   0.7606   0.1001
  -3.250   0.4275   0.01197   0.00550  -0.1769   0.7580   0.1092
  -3.000   0.4550   0.01181   0.00541  -0.1769   0.7554   0.1207
  -2.750   0.4835   0.01169   0.00533  -0.1771   0.7530   0.1375
  -2.500   0.5128   0.01153   0.00517  -0.1774   0.7505   0.1504
  -2.250   0.5429   0.01136   0.00503  -0.1779   0.7482   0.1628
  -2.000   0.5731   0.01130   0.00498  -0.1784   0.7457   0.1787
  -1.750   0.5992   0.01126   0.00496  -0.1780   0.7428   0.1931
  -1.500   0.6249   0.01111   0.00489  -0.1776   0.7394   0.2061
  -1.000   0.6806   0.01081   0.00471  -0.1777   0.7330   0.2497
  -0.750   0.7100   0.01062   0.00460  -0.1781   0.7303   0.2759
  -0.500   0.7402   0.01045   0.00446  -0.1785   0.7273   0.3113
  -0.250   0.7668   0.01030   0.00444  -0.1784   0.7237   0.3494
   0.000   0.7919   0.01012   0.00441  -0.1779   0.7195   0.3924
   0.250   0.8187   0.00987   0.00435  -0.1778   0.7156   0.4608
   0.500   0.8459   0.00957   0.00430  -0.1778   0.7122   0.5638
   0.750   0.8730   0.00936   0.00435  -0.1775   0.7091   0.6537
   1.000   0.8991   0.00935   0.00441  -0.1770   0.7051   0.7021
   1.250   0.9223   0.00935   0.00449  -0.1759   0.6999   0.7308
   1.500   0.9480   0.00932   0.00446  -0.1754   0.6945   0.7500
   1.750   0.9758   0.00929   0.00440  -0.1752   0.6896   0.7639
   2.000   0.9997   0.00934   0.00447  -0.1743   0.6842   0.7753
   2.250   1.0229   0.00937   0.00452  -0.1732   0.6778   0.7854
   2.500   1.0483   0.00938   0.00451  -0.1726   0.6721   0.7958
   2.750   1.0723   0.00943   0.00456  -0.1718   0.6659   0.8059
   3.000   1.0940   0.00947   0.00462  -0.1705   0.6582   0.8142
   3.250   1.1181   0.00950   0.00461  -0.1696   0.6512   0.8216
   3.500   1.1383   0.00959   0.00473  -0.1680   0.6426   0.8300
   3.750   1.1593   0.00966   0.00476  -0.1666   0.6332   0.8376
   4.000   1.1780   0.00978   0.00487  -0.1647   0.6224   0.8456
   4.250   1.1959   0.00989   0.00495  -0.1627   0.6112   0.8512
   4.500   1.2104   0.01001   0.00506  -0.1600   0.5986   0.8587
   4.750   1.2217   0.01015   0.00518  -0.1567   0.5862   0.8654
   5.000   1.2327   0.01040   0.00536  -0.1534   0.5736   0.8731
   5.250   1.2428   0.01065   0.00560  -0.1500   0.5596   0.8814
   5.500   1.2530   0.01093   0.00586  -0.1467   0.5466   0.8905
   5.750   1.2602   0.01128   0.00617  -0.1429   0.5323   0.9003
   6.000   1.2671   0.01168   0.00653  -0.1392   0.5184   0.9106
   6.250   1.2798   0.01209   0.00694  -0.1368   0.5054   0.9264
   6.500   1.3034   0.01256   0.00740  -0.1369   0.4917   1.0000
   6.750   1.3156   0.01316   0.00795  -0.1348   0.4772   1.0000
   7.000   1.3291   0.01376   0.00851  -0.1329   0.4646   1.0000
   7.250   1.3396   0.01451   0.00919  -0.1306   0.4523   1.0000
   7.500   1.3517   0.01524   0.00987  -0.1286   0.4404   1.0000
   7.750   1.3642   0.01599   0.01058  -0.1268   0.4284   1.0000
   8.000   1.3747   0.01685   0.01138  -0.1247   0.4157   1.0000
   8.250   1.3863   0.01770   0.01219  -0.1229   0.4014   1.0000
   8.500   1.3973   0.01861   0.01304  -0.1210   0.3900   1.0000
   8.750   1.4072   0.01960   0.01397  -0.1191   0.3786   1.0000
   9.000   1.4213   0.02040   0.01476  -0.1177   0.3690   1.0000
   9.250   1.4316   0.02141   0.01572  -0.1159   0.3572   1.0000
   9.500   1.4467   0.02219   0.01650  -0.1148   0.3477   1.0000
   9.750   1.4557   0.02332   0.01757  -0.1129   0.3363   1.0000
  10.000   1.4696   0.02419   0.01844  -0.1117   0.3277   1.0000
  10.250   1.4798   0.02529   0.01950  -0.1101   0.3193   1.0000
  10.500   1.4935   0.02621   0.02043  -0.1089   0.3117   1.0000
  10.750   1.5066   0.02717   0.02139  -0.1076   0.3035   1.0000
  11.000   1.5172   0.02832   0.02251  -0.1062   0.2958   1.0000
  11.250   1.5325   0.02919   0.02342  -0.1053   0.2884   1.0000
  11.500   1.5428   0.03040   0.02460  -0.1039   0.2799   1.0000
  11.750   1.5558   0.03143   0.02565  -0.1028   0.2733   1.0000
  12.000   1.5665   0.03264   0.02686  -0.1015   0.2662   1.0000
  12.250   1.5738   0.03413   0.02830  -0.1000   0.2589   1.0000
  12.500   1.5891   0.03505   0.02929  -0.0992   0.2535   1.0000
  12.750   1.5994   0.03635   0.03059  -0.0980   0.2460   1.0000
  13.000   1.6066   0.03791   0.03214  -0.0967   0.2394   1.0000
  13.250   1.6210   0.03894   0.03324  -0.0959   0.2329   1.0000
  13.500   1.6288   0.04051   0.03478  -0.0947   0.2241   1.0000
  13.750   1.6377   0.04203   0.03632  -0.0936   0.2174   1.0000
  14.000   1.6454   0.04365   0.03793  -0.0925   0.2105   1.0000
  14.250   1.6500   0.04554   0.03981  -0.0912   0.2040   1.0000
  14.500   1.6615   0.04689   0.04123  -0.0905   0.1984   1.0000
  14.750   1.6687   0.04860   0.04296  -0.0894   0.1921   1.0000
  15.000   1.6725   0.05068   0.04504  -0.0883   0.1856   1.0000
  15.250   1.6828   0.05219   0.04662  -0.0876   0.1788   1.0000
  15.500   1.6851   0.05447   0.04887  -0.0866   0.1702   1.0000
  15.750   1.6893   0.05659   0.05102  -0.0857   0.1634   1.0000
  16.000   1.6906   0.05902   0.05344  -0.0847   0.1570   1.0000
  16.250   1.6934   0.06137   0.05583  -0.0839   0.1517   1.0000
  16.500   1.6984   0.06351   0.05802  -0.0833   0.1456   1.0000
  16.750   1.6974   0.06632   0.06084  -0.0825   0.1398   1.0000
  17.000   1.7008   0.06869   0.06326  -0.0819   0.1340   1.0000
  17.250   1.7018   0.07137   0.06598  -0.0814   0.1275   1.0000
  17.500   1.6992   0.07451   0.06912  -0.0809   0.1216   1.0000
  17.750   1.6981   0.07753   0.07218  -0.0806   0.1164   1.0000
  18.000   1.6938   0.08098   0.07564  -0.0803   0.1116   1.0000
  18.250   1.6910   0.08431   0.07903  -0.0802   0.1074   1.0000
  18.500   1.6929   0.08707   0.08187  -0.0802   0.1036   1.0000
  18.750   1.6894   0.09058   0.08544  -0.0803   0.0995   1.0000
<< Back to FX 76-MP-160 (fx76mp160-il)

Polar data table (+)

Polar graphs


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