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NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-410 (naca65410-il)
Reynolds number: 50,000
Max Cl/Cd: 35.38 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65410-il-50000-n5.txt
Download as CSV file: xf-naca65410-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-410                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4435   0.09016   0.08327  -0.0446   1.0000   0.0666
  -8.250  -0.4730   0.08113   0.07444  -0.0498   1.0000   0.0572
  -8.000  -0.4782   0.07773   0.07111  -0.0495   1.0000   0.0558
  -7.750  -0.4865   0.07436   0.06776  -0.0492   1.0000   0.0545
  -7.500  -0.4957   0.07095   0.06436  -0.0487   1.0000   0.0533
  -7.250  -0.5043   0.06756   0.06092  -0.0479   1.0000   0.0520
  -7.000  -0.5111   0.06407   0.05732  -0.0470   1.0000   0.0507
  -6.750  -0.5156   0.06037   0.05341  -0.0461   1.0000   0.0493
  -6.500  -0.5163   0.05652   0.04923  -0.0453   1.0000   0.0479
  -6.250  -0.5118   0.05325   0.04567  -0.0443   1.0000   0.0479
  -6.000  -0.5041   0.05054   0.04279  -0.0433   1.0000   0.0494
  -5.750  -0.4940   0.04779   0.03976  -0.0425   1.0000   0.0510
  -5.500  -0.4810   0.04487   0.03647  -0.0419   1.0000   0.0520
  -5.250  -0.4651   0.04191   0.03302  -0.0413   1.0000   0.0520
  -5.000  -0.4467   0.03915   0.02980  -0.0408   1.0000   0.0521
  -4.750  -0.4246   0.03662   0.02679  -0.0406   0.9994   0.0526
  -4.500  -0.3902   0.03427   0.02386  -0.0424   0.9947   0.0559
  -4.250  -0.3558   0.03241   0.02135  -0.0437   0.9898   0.0589
  -4.000  -0.3228   0.03029   0.01903  -0.0449   0.9858   0.0608
  -3.750  -0.2920   0.02883   0.01738  -0.0454   0.9807   0.0633
  -3.500  -0.2593   0.02782   0.01618  -0.0463   0.9763   0.0700
  -3.250  -0.2306   0.02680   0.01502  -0.0463   0.9708   0.0751
  -3.000  -0.1987   0.02591   0.01400  -0.0473   0.9659   0.0808
  -2.750  -0.1695   0.02513   0.01305  -0.0481   0.9600   0.0908
  -2.500  -0.1374   0.02431   0.01221  -0.0497   0.9546   0.1107
  -2.250  -0.1034   0.02250   0.01123  -0.0525   0.9506   0.2390
  -2.000  -0.1051   0.02138   0.01233  -0.0444   0.9432   0.7483
  -1.750  -0.0959   0.02175   0.01276  -0.0377   0.9368   0.8487
  -1.500  -0.0282   0.02207   0.01277  -0.0410   0.9385   0.9729
  -1.250   0.0180   0.02205   0.01241  -0.0457   0.9336   0.9845
  -1.000   0.0629   0.02205   0.01212  -0.0503   0.9285   0.9983
  -0.750   0.0902   0.02210   0.01198  -0.0515   0.9218   1.0000
  -0.500   0.1075   0.02216   0.01190  -0.0509   0.9127   1.0000
  -0.250   0.1283   0.02227   0.01187  -0.0508   0.9051   1.0000
   0.000   0.1530   0.02243   0.01188  -0.0513   0.8979   1.0000
   0.250   0.1781   0.02263   0.01196  -0.0519   0.8910   1.0000
   0.500   0.2048   0.02286   0.01210  -0.0526   0.8843   1.0000
   0.750   0.2360   0.02312   0.01226  -0.0541   0.8788   1.0000
   1.000   0.2595   0.02343   0.01251  -0.0542   0.8712   1.0000
   1.250   0.2950   0.02369   0.01273  -0.0563   0.8667   1.0000
   1.500   0.3154   0.02409   0.01310  -0.0559   0.8583   1.0000
   1.750   0.3496   0.02438   0.01341  -0.0576   0.8533   1.0000
   2.000   0.3718   0.02482   0.01386  -0.0574   0.8454   1.0000
   2.250   0.4042   0.02515   0.01423  -0.0588   0.8398   1.0000
   2.500   0.4282   0.02561   0.01474  -0.0589   0.8322   1.0000
   2.750   0.4592   0.02597   0.01521  -0.0600   0.8259   1.0000
   3.000   0.4842   0.02643   0.01577  -0.0601   0.8182   1.0000
   3.250   0.5153   0.02679   0.01626  -0.0611   0.8114   1.0000
   3.500   0.5393   0.02727   0.01691  -0.0609   0.8026   1.0000
   3.750   0.5743   0.02750   0.01734  -0.0623   0.7959   1.0000
   4.000   0.5969   0.02797   0.01799  -0.0618   0.7853   1.0000
   4.250   0.6269   0.02825   0.01850  -0.0622   0.7762   1.0000
   4.500   0.6603   0.02836   0.01894  -0.0628   0.7671   1.0000
   4.750   0.6864   0.02859   0.01945  -0.0624   0.7545   1.0000
   5.000   0.7336   0.02621   0.01745  -0.0608   0.7193   1.0000
   5.250   0.7621   0.02247   0.01367  -0.0534   0.6060   1.0000
   5.500   0.7811   0.02208   0.01241  -0.0486   0.3928   1.0000
   5.750   0.7716   0.02510   0.01371  -0.0437   0.1720   1.0000
   6.000   0.7754   0.02745   0.01540  -0.0411   0.1104   1.0000
   6.250   0.7869   0.02912   0.01698  -0.0392   0.0917   1.0000
   6.500   0.7996   0.03069   0.01856  -0.0373   0.0827   1.0000
   6.750   0.8155   0.03211   0.02007  -0.0358   0.0741   1.0000
   7.000   0.8359   0.03359   0.02170  -0.0348   0.0668   1.0000
   7.250   0.8678   0.03520   0.02347  -0.0349   0.0618   1.0000
   7.500   0.9099   0.03735   0.02566  -0.0363   0.0573   1.0000
   7.750   0.9439   0.03935   0.02800  -0.0368   0.0524   1.0000
   8.000   0.9760   0.04186   0.03082  -0.0373   0.0498   1.0000
   8.250   1.0041   0.04477   0.03400  -0.0374   0.0482   1.0000
   8.500   1.0277   0.04811   0.03764  -0.0371   0.0472   1.0000
   8.750   1.0455   0.05185   0.04171  -0.0363   0.0462   1.0000
   9.000   1.0544   0.05486   0.04533  -0.0342   0.0451   1.0000
   9.250   1.0591   0.05813   0.04915  -0.0320   0.0438   1.0000
   9.500   1.0600   0.06165   0.05313  -0.0298   0.0429   1.0000
   9.750   1.0573   0.06537   0.05725  -0.0276   0.0426   1.0000
  10.000   1.0503   0.06915   0.06138  -0.0254   0.0426   1.0000
  10.250   1.0382   0.07276   0.06527  -0.0230   0.0427   1.0000
  10.500   1.0231   0.07654   0.06929  -0.0211   0.0428   1.0000
  10.750   1.0057   0.08066   0.07362  -0.0201   0.0430   1.0000
  11.000   0.9865   0.08526   0.07841  -0.0201   0.0432   1.0000
  11.250   0.9664   0.09042   0.08374  -0.0213   0.0435   1.0000
  11.500   0.9463   0.09626   0.08970  -0.0236   0.0438   1.0000
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