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NACA 1410 (naca1410-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 1410 (naca1410-il)
Reynolds number: 100,000
Max Cl/Cd: 42.16 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca1410-il-100000-n5.txt
Download as CSV file: xf-naca1410-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7027   0.08728   0.08206  -0.0185   1.0000   0.0351
 -11.000  -0.7306   0.07546   0.07022  -0.0276   1.0000   0.0347
 -10.750  -0.7576   0.06629   0.06093  -0.0359   1.0000   0.0343
 -10.500  -0.7837   0.06003   0.05451  -0.0397   1.0000   0.0340
 -10.250  -0.8073   0.05510   0.04932  -0.0397   1.0000   0.0341
 -10.000  -0.8236   0.05014   0.04392  -0.0391   1.0000   0.0346
  -9.750  -0.8320   0.04567   0.03886  -0.0378   1.0000   0.0352
  -9.500  -0.8257   0.04261   0.03560  -0.0368   1.0000   0.0360
  -9.250  -0.8138   0.04066   0.03352  -0.0358   1.0000   0.0373
  -9.000  -0.8007   0.03884   0.03150  -0.0347   1.0000   0.0391
  -8.750  -0.7882   0.03657   0.02888  -0.0335   1.0000   0.0412
  -8.500  -0.7749   0.03403   0.02585  -0.0320   1.0000   0.0431
  -8.250  -0.7591   0.03181   0.02326  -0.0307   1.0000   0.0450
  -8.000  -0.7404   0.03051   0.02195  -0.0298   1.0000   0.0473
  -7.750  -0.7212   0.02920   0.02044  -0.0288   1.0000   0.0497
  -7.500  -0.7015   0.02771   0.01868  -0.0276   1.0000   0.0521
  -7.250  -0.6808   0.02652   0.01716  -0.0264   1.0000   0.0549
  -7.000  -0.6609   0.02516   0.01583  -0.0254   1.0000   0.0575
  -6.750  -0.6400   0.02411   0.01471  -0.0244   1.0000   0.0598
  -6.500  -0.6188   0.02317   0.01364  -0.0233   1.0000   0.0631
  -6.250  -0.5971   0.02233   0.01261  -0.0221   1.0000   0.0666
  -6.000  -0.5768   0.02131   0.01163  -0.0210   1.0000   0.0697
  -5.750  -0.5558   0.02051   0.01081  -0.0199   1.0000   0.0732
  -5.500  -0.5346   0.01978   0.00999  -0.0187   1.0000   0.0776
  -5.250  -0.5138   0.01904   0.00924  -0.0176   1.0000   0.0834
  -5.000  -0.4923   0.01843   0.00861  -0.0165   1.0000   0.0923
  -4.750  -0.4713   0.01776   0.00800  -0.0154   1.0000   0.1032
  -4.500  -0.4497   0.01716   0.00745  -0.0144   1.0000   0.1184
  -4.250  -0.4279   0.01661   0.00697  -0.0135   1.0000   0.1396
  -4.000  -0.4059   0.01611   0.00660  -0.0127   1.0000   0.1695
  -3.750  -0.3838   0.01565   0.00631  -0.0120   1.0000   0.2075
  -3.500  -0.3615   0.01521   0.00607  -0.0113   1.0000   0.2546
  -3.250  -0.3392   0.01474   0.00583  -0.0106   1.0000   0.3096
  -3.000  -0.3172   0.01421   0.00569  -0.0099   1.0000   0.3772
  -2.750  -0.2950   0.01385   0.00567  -0.0090   1.0000   0.4626
  -2.500  -0.2638   0.01360   0.00558  -0.0099   0.9961   0.5301
  -2.250  -0.2274   0.01331   0.00555  -0.0116   0.9888   0.5951
  -2.000  -0.1918   0.01308   0.00556  -0.0129   0.9813   0.6647
  -1.750  -0.1553   0.01293   0.00560  -0.0142   0.9739   0.7314
  -1.500  -0.1209   0.01282   0.00564  -0.0149   0.9648   0.7903
  -1.250  -0.0825   0.01279   0.00568  -0.0163   0.9570   0.8443
  -1.000  -0.0386   0.01279   0.00571  -0.0190   0.9496   0.8907
  -0.750   0.0074   0.01280   0.00569  -0.0222   0.9414   0.9287
  -0.500   0.0586   0.01279   0.00564  -0.0267   0.9337   0.9592
  -0.250   0.1097   0.01274   0.00555  -0.0314   0.9236   0.9809
   0.000   0.1627   0.01264   0.00541  -0.0365   0.9129   0.9960
   0.250   0.1999   0.01253   0.00526  -0.0385   0.8963   1.0000
   0.500   0.2297   0.01244   0.00513  -0.0388   0.8769   1.0000
   0.750   0.2593   0.01235   0.00500  -0.0389   0.8571   1.0000
   1.000   0.2861   0.01231   0.00491  -0.0384   0.8347   1.0000
   1.250   0.3130   0.01228   0.00481  -0.0378   0.8121   1.0000
   1.500   0.3383   0.01229   0.00478  -0.0370   0.7877   1.0000
   1.750   0.3638   0.01232   0.00474  -0.0362   0.7635   1.0000
   2.000   0.3885   0.01239   0.00475  -0.0352   0.7377   1.0000
   2.250   0.4130   0.01249   0.00479  -0.0342   0.7113   1.0000
   2.500   0.4372   0.01262   0.00483  -0.0331   0.6838   1.0000
   2.750   0.4611   0.01278   0.00490  -0.0320   0.6553   1.0000
   3.000   0.4849   0.01298   0.00502  -0.0309   0.6264   1.0000
   3.250   0.5084   0.01320   0.00515  -0.0298   0.5966   1.0000
   3.500   0.5317   0.01345   0.00530  -0.0287   0.5650   1.0000
   3.750   0.5548   0.01372   0.00549  -0.0275   0.5306   1.0000
   4.000   0.5777   0.01403   0.00570  -0.0264   0.4957   1.0000
   4.250   0.6005   0.01437   0.00594  -0.0253   0.4606   1.0000
   4.500   0.6227   0.01477   0.00621  -0.0242   0.4173   1.0000
   4.750   0.6437   0.01527   0.00647  -0.0229   0.3617   1.0000
   5.000   0.6642   0.01589   0.00680  -0.0217   0.3007   1.0000
   5.250   0.6850   0.01658   0.00723  -0.0207   0.2475   1.0000
   5.500   0.7058   0.01732   0.00776  -0.0197   0.1978   1.0000
   5.750   0.7265   0.01814   0.00836  -0.0187   0.1560   1.0000
   6.000   0.7474   0.01897   0.00906  -0.0177   0.1253   1.0000
   6.250   0.7680   0.01985   0.00984  -0.0167   0.1043   1.0000
   6.500   0.7885   0.02074   0.01072  -0.0156   0.0909   1.0000
   6.750   0.8087   0.02164   0.01162  -0.0145   0.0816   1.0000
   7.000   0.8284   0.02259   0.01254  -0.0134   0.0746   1.0000
   7.250   0.8487   0.02351   0.01356  -0.0122   0.0700   1.0000
   7.500   0.8690   0.02448   0.01463  -0.0111   0.0663   1.0000
   7.750   0.8886   0.02553   0.01571  -0.0100   0.0632   1.0000
   8.000   0.9082   0.02674   0.01695  -0.0089   0.0601   1.0000
   8.250   0.9291   0.02779   0.01818  -0.0079   0.0568   1.0000
   8.500   0.9495   0.02902   0.01951  -0.0070   0.0544   1.0000
   8.750   0.9691   0.03025   0.02079  -0.0060   0.0519   1.0000
   9.000   0.9881   0.03184   0.02246  -0.0051   0.0494   1.0000
   9.250   1.0074   0.03333   0.02424  -0.0041   0.0471   1.0000
   9.500   1.0253   0.03494   0.02608  -0.0029   0.0448   1.0000
   9.750   1.0417   0.03636   0.02763  -0.0018   0.0425   1.0000
  10.000   1.0574   0.03807   0.02936  -0.0009   0.0405   1.0000
  10.250   1.0699   0.04045   0.03206   0.0006   0.0391   1.0000
  10.500   1.0786   0.04281   0.03487   0.0024   0.0374   1.0000
  10.750   1.0851   0.04507   0.03746   0.0042   0.0357   1.0000
  11.000   1.0896   0.04721   0.03984   0.0060   0.0342   1.0000
  11.250   1.0916   0.04943   0.04225   0.0078   0.0333   1.0000
  11.500   1.0899   0.05180   0.04479   0.0099   0.0326   1.0000
  11.750   1.0867   0.05445   0.04757   0.0116   0.0319   1.0000
  12.000   1.0777   0.05786   0.05114   0.0130   0.0314   1.0000
  12.250   1.0591   0.06194   0.05554   0.0135   0.0312   1.0000
  12.500   1.0384   0.06683   0.06073   0.0126   0.0310   1.0000
  12.750   1.0162   0.07267   0.06683   0.0100   0.0310   1.0000
  13.000   0.9924   0.07958   0.07396   0.0059   0.0311   1.0000
  13.250   0.9673   0.08766   0.08222   0.0006   0.0312   1.0000
  13.500   0.9413   0.09688   0.09158  -0.0057   0.0315   1.0000
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