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

NACA 1410 (naca1410-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 1410 (naca1410-il)
Reynolds number: 200,000
Max Cl/Cd: 50.59 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1410-il-200000-n5.txt
Download as CSV file: xf-naca1410-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 1410                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8647   0.06544   0.06159  -0.0294   1.0000   0.0184
 -12.000  -0.9111   0.05265   0.04842  -0.0410   1.0000   0.0180
 -11.750  -0.9312   0.04743   0.04293  -0.0436   1.0000   0.0181
 -11.500  -0.9443   0.04401   0.03928  -0.0428   1.0000   0.0183
 -11.250  -0.9503   0.04111   0.03611  -0.0414   1.0000   0.0187
 -11.000  -0.9502   0.03829   0.03299  -0.0400   1.0000   0.0193
 -10.750  -0.9460   0.03565   0.02998  -0.0386   1.0000   0.0202
 -10.500  -0.9380   0.03321   0.02709  -0.0372   1.0000   0.0212
 -10.250  -0.9250   0.03155   0.02526  -0.0360   1.0000   0.0220
 -10.000  -0.9079   0.03056   0.02422  -0.0351   1.0000   0.0229
  -9.750  -0.8908   0.02940   0.02291  -0.0341   1.0000   0.0239
  -9.500  -0.8738   0.02802   0.02132  -0.0330   1.0000   0.0251
  -9.250  -0.8557   0.02673   0.01974  -0.0319   1.0000   0.0267
  -9.000  -0.8373   0.02543   0.01822  -0.0308   1.0000   0.0281
  -8.750  -0.8182   0.02444   0.01717  -0.0298   1.0000   0.0295
  -8.500  -0.7982   0.02358   0.01623  -0.0288   1.0000   0.0309
  -8.250  -0.7777   0.02275   0.01526  -0.0278   1.0000   0.0328
  -8.000  -0.7568   0.02197   0.01429  -0.0267   1.0000   0.0346
  -7.750  -0.7371   0.02090   0.01313  -0.0255   1.0000   0.0362
  -7.500  -0.7169   0.02012   0.01230  -0.0244   1.0000   0.0380
  -7.250  -0.6958   0.01950   0.01163  -0.0234   1.0000   0.0400
  -7.000  -0.6745   0.01886   0.01090  -0.0223   1.0000   0.0420
  -6.750  -0.6530   0.01826   0.01019  -0.0212   1.0000   0.0437
  -6.500  -0.6325   0.01749   0.00939  -0.0200   1.0000   0.0457
  -6.250  -0.6116   0.01687   0.00875  -0.0189   1.0000   0.0479
  -6.000  -0.5902   0.01635   0.00818  -0.0178   1.0000   0.0499
  -5.750  -0.5685   0.01589   0.00766  -0.0167   1.0000   0.0524
  -5.500  -0.5465   0.01548   0.00718  -0.0157   1.0000   0.0549
  -5.250  -0.5251   0.01493   0.00664  -0.0147   1.0000   0.0584
  -5.000  -0.5029   0.01453   0.00622  -0.0137   1.0000   0.0624
  -4.750  -0.4803   0.01419   0.00584  -0.0128   1.0000   0.0674
  -4.500  -0.4478   0.01374   0.00543  -0.0141   0.9969   0.0778
  -4.250  -0.4123   0.01331   0.00505  -0.0160   0.9929   0.0957
  -4.000  -0.3774   0.01288   0.00474  -0.0178   0.9881   0.1211
  -3.750  -0.3413   0.01250   0.00447  -0.0198   0.9838   0.1512
  -3.500  -0.3074   0.01213   0.00422  -0.0213   0.9779   0.1838
  -3.250  -0.2706   0.01177   0.00401  -0.0234   0.9736   0.2225
  -3.000  -0.2383   0.01139   0.00382  -0.0245   0.9663   0.2722
  -2.750  -0.2036   0.01088   0.00361  -0.0263   0.9611   0.3371
  -2.500  -0.1750   0.01035   0.00352  -0.0266   0.9519   0.4328
  -2.250  -0.1424   0.01008   0.00340  -0.0276   0.9444   0.4934
  -2.000  -0.1116   0.00984   0.00327  -0.0281   0.9348   0.5328
  -1.750  -0.0818   0.00959   0.00318  -0.0283   0.9245   0.5747
  -1.500  -0.0518   0.00930   0.00310  -0.0285   0.9146   0.6251
  -1.250  -0.0236   0.00907   0.00304  -0.0282   0.9026   0.6748
  -1.000   0.0039   0.00887   0.00299  -0.0276   0.8894   0.7208
  -0.750   0.0312   0.00872   0.00296  -0.0269   0.8754   0.7656
  -0.500   0.0584   0.00860   0.00296  -0.0261   0.8603   0.8109
  -0.250   0.0866   0.00854   0.00296  -0.0255   0.8441   0.8550
   0.000   0.1178   0.00853   0.00296  -0.0254   0.8265   0.8914
   0.250   0.1510   0.00856   0.00296  -0.0260   0.8063   0.9204
   0.500   0.1852   0.00862   0.00294  -0.0269   0.7840   0.9412
   0.750   0.2197   0.00869   0.00292  -0.0279   0.7605   0.9580
   1.000   0.2547   0.00877   0.00290  -0.0291   0.7359   0.9719
   1.250   0.2910   0.00887   0.00290  -0.0308   0.7101   0.9836
   1.500   0.3293   0.00898   0.00290  -0.0329   0.6825   0.9928
   1.750   0.3658   0.00912   0.00291  -0.0347   0.6524   1.0000
   2.000   0.3896   0.00926   0.00292  -0.0338   0.6240   1.0000
   2.250   0.4135   0.00943   0.00297  -0.0330   0.5965   1.0000
   2.500   0.4373   0.00960   0.00304  -0.0321   0.5689   1.0000
   2.750   0.4609   0.00982   0.00312  -0.0312   0.5379   1.0000
   3.000   0.4841   0.01006   0.00323  -0.0303   0.5049   1.0000
   3.250   0.5076   0.01030   0.00335  -0.0294   0.4746   1.0000
   3.500   0.5307   0.01057   0.00350  -0.0285   0.4404   1.0000
   3.750   0.5530   0.01093   0.00367  -0.0274   0.3953   1.0000
   4.000   0.5748   0.01137   0.00385  -0.0264   0.3395   1.0000
   4.250   0.5967   0.01185   0.00409  -0.0254   0.2875   1.0000
   4.500   0.6194   0.01230   0.00437  -0.0246   0.2470   1.0000
   4.750   0.6422   0.01277   0.00468  -0.0238   0.2089   1.0000
   5.000   0.6649   0.01329   0.00504  -0.0230   0.1726   1.0000
   5.250   0.6876   0.01382   0.00542  -0.0222   0.1403   1.0000
   5.500   0.7103   0.01438   0.00587  -0.0215   0.1114   1.0000
   5.750   0.7328   0.01498   0.00634  -0.0207   0.0881   1.0000
   6.000   0.7556   0.01557   0.00686  -0.0199   0.0729   1.0000
   6.250   0.7786   0.01611   0.00741  -0.0192   0.0637   1.0000
   6.500   0.8015   0.01667   0.00799  -0.0184   0.0584   1.0000
   6.750   0.8244   0.01723   0.00860  -0.0176   0.0545   1.0000
   7.000   0.8463   0.01790   0.00928  -0.0167   0.0512   1.0000
   7.250   0.8682   0.01857   0.01000  -0.0158   0.0487   1.0000
   7.500   0.8904   0.01919   0.01072  -0.0150   0.0464   1.0000
   7.750   0.9121   0.01987   0.01148  -0.0141   0.0444   1.0000
   8.000   0.9333   0.02060   0.01225  -0.0132   0.0424   1.0000
   8.250   0.9520   0.02166   0.01331  -0.0121   0.0402   1.0000
   8.500   0.9732   0.02241   0.01418  -0.0111   0.0387   1.0000
   8.750   0.9941   0.02320   0.01510  -0.0102   0.0369   1.0000
   9.000   1.0145   0.02400   0.01599  -0.0093   0.0350   1.0000
   9.250   1.0339   0.02486   0.01691  -0.0083   0.0334   1.0000
   9.500   1.0508   0.02614   0.01820  -0.0071   0.0317   1.0000
   9.750   1.0697   0.02713   0.01936  -0.0060   0.0303   1.0000
  10.000   1.0879   0.02814   0.02057  -0.0049   0.0287   1.0000
  10.250   1.1050   0.02921   0.02177  -0.0037   0.0273   1.0000
  10.500   1.1209   0.03020   0.02285  -0.0025   0.0260   1.0000
  10.750   1.1346   0.03144   0.02413  -0.0011   0.0248   1.0000
  11.000   1.1471   0.03290   0.02578   0.0004   0.0237   1.0000
  11.250   1.1582   0.03439   0.02752   0.0022   0.0226   1.0000
  11.500   1.1656   0.03593   0.02927   0.0043   0.0217   1.0000
  11.750   1.1717   0.03743   0.03094   0.0063   0.0208   1.0000
  12.000   1.1771   0.03888   0.03254   0.0081   0.0201   1.0000
  12.250   1.1816   0.04039   0.03414   0.0095   0.0195   1.0000
  12.500   1.1841   0.04220   0.03604   0.0108   0.0190   1.0000
  12.750   1.1821   0.04477   0.03879   0.0118   0.0185   1.0000
  13.000   1.1769   0.04793   0.04225   0.0123   0.0180   1.0000
  13.250   1.1690   0.05161   0.04621   0.0122   0.0175   1.0000
  13.500   1.1586   0.05589   0.05074   0.0112   0.0172   1.0000
  13.750   1.1456   0.06089   0.05598   0.0093   0.0169   1.0000
  14.000   1.1298   0.06674   0.06207   0.0064   0.0168   1.0000
  14.250   1.1103   0.07367   0.06923   0.0024   0.0167   1.0000
  14.500   1.0861   0.08201   0.07780  -0.0028   0.0167   1.0000
  14.750   1.0556   0.09226   0.08827  -0.0093   0.0169   1.0000
  15.000   1.0155   0.10553   0.10175  -0.0177   0.0172   1.0000
<< Back to NACA 1410 (naca1410-il)

Polar data table (+)

Polar graphs


<< Back to NACA 1410 (naca1410-il)