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Falcon (falcon-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Falcon (falcon-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.57 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-falcon-il-1000000.txt
Download as CSV file: xf-falcon-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Falcon                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -1.1009   0.07843   0.07562  -0.0311   1.0000   0.0116
 -16.750  -1.1335   0.06886   0.06585  -0.0368   1.0000   0.0116
 -16.500  -1.1541   0.06173   0.05858  -0.0409   1.0000   0.0116
 -16.250  -1.1706   0.05568   0.05238  -0.0442   1.0000   0.0117
 -16.000  -1.1830   0.05062   0.04718  -0.0467   1.0000   0.0117
 -15.750  -1.1903   0.04659   0.04303  -0.0482   1.0000   0.0118
 -15.500  -1.1957   0.04312   0.03944  -0.0491   1.0000   0.0119
 -15.250  -1.1988   0.04019   0.03640  -0.0493   1.0000   0.0120
 -15.000  -1.1990   0.03778   0.03390  -0.0491   1.0000   0.0121
 -14.750  -1.1998   0.03550   0.03151  -0.0483   1.0000   0.0123
 -14.500  -1.1985   0.03358   0.02949  -0.0471   1.0000   0.0124
 -14.250  -1.1953   0.03195   0.02776  -0.0457   1.0000   0.0126
 -14.000  -1.1928   0.03039   0.02609  -0.0438   1.0000   0.0127
 -13.750  -1.1883   0.02908   0.02468  -0.0417   1.0000   0.0129
 -13.500  -1.1836   0.02789   0.02339  -0.0393   1.0000   0.0131
 -13.250  -1.1768   0.02693   0.02234  -0.0367   1.0000   0.0133
 -13.000  -1.1700   0.02605   0.02137  -0.0338   1.0000   0.0134
 -12.750  -1.1624   0.02532   0.02056  -0.0308   1.0000   0.0135
 -12.500  -1.1538   0.02464   0.01980  -0.0278   1.0000   0.0137
 -12.250  -1.1506   0.02312   0.01815  -0.0243   1.0000   0.0140
 -12.000  -1.1421   0.02194   0.01689  -0.0215   1.0000   0.0143
 -11.750  -1.1276   0.02117   0.01607  -0.0195   1.0000   0.0147
 -11.500  -1.1108   0.02054   0.01540  -0.0178   1.0000   0.0150
 -11.250  -1.0927   0.01999   0.01480  -0.0163   1.0000   0.0153
 -11.000  -1.0741   0.01945   0.01422  -0.0148   1.0000   0.0157
 -10.750  -1.0549   0.01894   0.01366  -0.0134   1.0000   0.0162
 -10.500  -1.0349   0.01848   0.01315  -0.0121   1.0000   0.0166
 -10.250  -1.0148   0.01803   0.01264  -0.0108   1.0000   0.0169
 -10.000  -0.9945   0.01759   0.01215  -0.0094   1.0000   0.0172
  -9.750  -0.9815   0.01651   0.01100  -0.0069   1.0000   0.0179
  -9.500  -0.9631   0.01598   0.01045  -0.0053   1.0000   0.0184
  -9.250  -0.9441   0.01557   0.01002  -0.0036   1.0000   0.0189
  -9.000  -0.9267   0.01522   0.00965  -0.0017   1.0000   0.0195
  -8.750  -0.8975   0.01479   0.00919  -0.0022   0.9991   0.0202
  -8.500  -0.8641   0.01438   0.00874  -0.0036   0.9974   0.0208
  -8.250  -0.8322   0.01382   0.00813  -0.0047   0.9946   0.0216
  -8.000  -0.8084   0.01319   0.00749  -0.0041   0.9790   0.0227
  -7.750  -0.7761   0.01279   0.00708  -0.0052   0.9739   0.0238
  -7.500  -0.7413   0.01240   0.00666  -0.0068   0.9700   0.0249
  -7.250  -0.7037   0.01205   0.00628  -0.0090   0.9668   0.0258
  -7.000  -0.6665   0.01143   0.00564  -0.0113   0.9629   0.0279
  -6.750  -0.6242   0.01107   0.00528  -0.0146   0.9595   0.0300
  -6.500  -0.5786   0.01066   0.00485  -0.0188   0.9559   0.0325
  -6.250  -0.5362   0.01026   0.00446  -0.0222   0.9492   0.0362
  -5.750  -0.4656   0.00972   0.00388  -0.0257   0.9291   0.0453
  -5.500  -0.4391   0.00947   0.00364  -0.0254   0.9168   0.0524
  -5.250  -0.4133   0.00926   0.00344  -0.0249   0.9039   0.0603
  -5.000  -0.3878   0.00908   0.00326  -0.0243   0.8899   0.0692
  -4.750  -0.3626   0.00893   0.00310  -0.0237   0.8739   0.0776
  -4.500  -0.3379   0.00877   0.00294  -0.0229   0.8558   0.0879
  -4.250  -0.3133   0.00865   0.00278  -0.0221   0.8348   0.0970
  -4.000  -0.2885   0.00859   0.00264  -0.0213   0.8122   0.1043
  -3.750  -0.2645   0.00848   0.00250  -0.0203   0.7874   0.1153
  -3.500  -0.2404   0.00842   0.00237  -0.0194   0.7627   0.1260
  -3.250  -0.2163   0.00835   0.00225  -0.0185   0.7370   0.1381
  -3.000  -0.1923   0.00828   0.00214  -0.0176   0.7130   0.1532
  -2.750  -0.1688   0.00815   0.00202  -0.0166   0.6899   0.1767
  -2.500  -0.1479   0.00782   0.00184  -0.0152   0.6693   0.2368
  -2.250  -0.1319   0.00716   0.00166  -0.0129   0.6515   0.3851
  -2.000  -0.1102   0.00692   0.00158  -0.0116   0.6343   0.4482
  -1.750  -0.0878   0.00673   0.00152  -0.0104   0.6181   0.5033
  -1.500  -0.0650   0.00657   0.00147  -0.0092   0.6033   0.5519
  -1.250  -0.0418   0.00644   0.00143  -0.0081   0.5893   0.5934
  -1.000  -0.0189   0.00631   0.00140  -0.0070   0.5760   0.6373
  -0.750   0.0043   0.00622   0.00138  -0.0058   0.5637   0.6768
  -0.500   0.0277   0.00616   0.00138  -0.0047   0.5512   0.7130
  -0.250   0.0516   0.00612   0.00139  -0.0037   0.5385   0.7441
   0.000   0.0764   0.00610   0.00140  -0.0029   0.5264   0.7690
   0.250   0.1013   0.00610   0.00142  -0.0021   0.5145   0.7918
   0.500   0.1266   0.00612   0.00144  -0.0013   0.5025   0.8114
   0.750   0.1522   0.00615   0.00146  -0.0007   0.4899   0.8283
   1.000   0.1781   0.00617   0.00149  -0.0001   0.4773   0.8456
   1.250   0.2041   0.00620   0.00152   0.0004   0.4649   0.8629
   1.500   0.2305   0.00625   0.00157   0.0009   0.4526   0.8805
   1.750   0.2577   0.00631   0.00162   0.0011   0.4400   0.8984
   2.000   0.2854   0.00636   0.00166   0.0012   0.4275   0.9123
   2.250   0.3167   0.00643   0.00171   0.0005   0.4152   0.9222
   2.500   0.3488   0.00652   0.00176  -0.0004   0.4037   0.9320
   2.750   0.3816   0.00662   0.00182  -0.0016   0.3915   0.9421
   3.000   0.4232   0.00674   0.00190  -0.0048   0.3784   0.9475
   3.250   0.4642   0.00686   0.00199  -0.0078   0.3672   0.9532
   3.500   0.5061   0.00701   0.00209  -0.0111   0.3548   0.9573
   3.750   0.5487   0.00718   0.00221  -0.0146   0.3424   0.9602
   4.000   0.5893   0.00736   0.00235  -0.0175   0.3311   0.9638
   4.250   0.6263   0.00753   0.00249  -0.0196   0.3209   0.9683
   4.500   0.6632   0.00773   0.00265  -0.0217   0.3101   0.9708
   5.000   0.7307   0.00813   0.00296  -0.0244   0.2882   0.9775
   5.250   0.7637   0.00833   0.00313  -0.0257   0.2781   0.9815
   5.500   0.7947   0.00857   0.00332  -0.0265   0.2674   0.9868
   5.750   0.8269   0.00877   0.00351  -0.0276   0.2575   0.9925
   6.000   0.8604   0.00902   0.00371  -0.0290   0.2464   0.9954
   6.250   0.8958   0.00924   0.00389  -0.0309   0.2337   0.9971
   6.500   0.9303   0.00950   0.00407  -0.0326   0.2176   0.9987
   6.750   0.9640   0.00978   0.00428  -0.0341   0.2014   0.9999
   7.000   0.9851   0.01001   0.00445  -0.0330   0.1905   1.0000
   7.250   1.0050   0.01020   0.00462  -0.0315   0.1819   1.0000
   7.500   1.0255   0.01043   0.00482  -0.0302   0.1727   1.0000
   8.000   1.0684   0.01094   0.00527  -0.0279   0.1556   1.0000
   8.250   1.0899   0.01124   0.00553  -0.0268   0.1470   1.0000
   8.500   1.1120   0.01151   0.00578  -0.0258   0.1394   1.0000
   8.750   1.1341   0.01181   0.00606  -0.0248   0.1324   1.0000
   9.000   1.1560   0.01212   0.00634  -0.0238   0.1246   1.0000
   9.250   1.1779   0.01245   0.00665  -0.0229   0.1161   1.0000
   9.500   1.1982   0.01289   0.00703  -0.0217   0.1031   1.0000
   9.750   1.2144   0.01364   0.00760  -0.0199   0.0778   1.0000
  10.000   1.2148   0.01552   0.00908  -0.0157   0.0257   1.0000
  10.250   1.2309   0.01624   0.00979  -0.0138   0.0201   1.0000
  10.500   1.2485   0.01682   0.01039  -0.0123   0.0179   1.0000
  10.750   1.2646   0.01749   0.01110  -0.0105   0.0163   1.0000
  11.000   1.2824   0.01800   0.01166  -0.0090   0.0155   1.0000
  11.250   1.2987   0.01860   0.01230  -0.0073   0.0147   1.0000
  11.500   1.3132   0.01929   0.01303  -0.0054   0.0140   1.0000
  11.750   1.3215   0.02014   0.01394  -0.0024   0.0133   1.0000
  12.000   1.3274   0.02090   0.01477   0.0010   0.0129   1.0000
  12.250   1.3373   0.02155   0.01548   0.0035   0.0126   1.0000
  12.500   1.3460   0.02234   0.01634   0.0060   0.0123   1.0000
  12.750   1.3540   0.02326   0.01732   0.0083   0.0119   1.0000
  13.000   1.3616   0.02430   0.01842   0.0103   0.0116   1.0000
  13.250   1.3680   0.02551   0.01969   0.0122   0.0113   1.0000
  13.500   1.3729   0.02694   0.02119   0.0139   0.0111   1.0000
  13.750   1.3755   0.02867   0.02300   0.0154   0.0108   1.0000
  14.000   1.3736   0.03096   0.02539   0.0166   0.0106   1.0000
  14.250   1.3681   0.03386   0.02841   0.0174   0.0104   1.0000
  14.500   1.3584   0.03752   0.03220   0.0175   0.0102   1.0000
  14.750   1.3581   0.04039   0.03517   0.0173   0.0101   1.0000
  15.000   1.3576   0.04342   0.03829   0.0168   0.0100   1.0000
  15.250   1.3534   0.04700   0.04198   0.0160   0.0100   1.0000
  15.500   1.3476   0.05087   0.04595   0.0150   0.0099   1.0000
  15.750   1.3381   0.05532   0.05051   0.0138   0.0098   1.0000
  16.000   1.3280   0.05987   0.05517   0.0125   0.0097   1.0000
  16.250   1.3164   0.06477   0.06018   0.0110   0.0097   1.0000
  16.500   1.3027   0.07008   0.06561   0.0092   0.0096   1.0000
  16.750   1.2896   0.07540   0.07103   0.0074   0.0095   1.0000
  17.000   1.2742   0.08120   0.07694   0.0053   0.0095   1.0000
  17.250   1.2598   0.08690   0.08274   0.0032   0.0095   1.0000
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