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

NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 66(2)-215 (naca662215-il)
Reynolds number: 200,000
Max Cl/Cd: 44.82 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca662215-il-200000.txt
Download as CSV file: xf-naca662215-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(2)-215                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4837   0.10242   0.09890  -0.0634   1.0000   0.0684
 -12.000  -0.4910   0.10140   0.09795  -0.0603   1.0000   0.0693
 -11.750  -0.5138   0.10051   0.09715  -0.0561   0.9995   0.0699
 -11.500  -0.5077   0.09508   0.09171  -0.0608   0.9963   0.0720
 -11.250  -0.5250   0.08463   0.08123  -0.0713   0.9914   0.0738
 -11.000  -0.5520   0.07591   0.07239  -0.0796   0.9862   0.0748
 -10.750  -0.5793   0.06970   0.06596  -0.0845   0.9803   0.0762
 -10.500  -0.6236   0.06704   0.06280  -0.0858   0.9707   0.0784
 -10.000  -0.6145   0.05722   0.05285  -0.0875   0.9612   0.0824
  -9.750  -0.5966   0.05438   0.04993  -0.0889   0.9585   0.0855
  -9.500  -0.6020   0.05267   0.04800  -0.0861   0.9504   0.0891
  -8.750  -0.6193   0.03793   0.03123  -0.0735   0.9318   0.0567
  -8.500  -0.5915   0.03468   0.02770  -0.0737   0.9300   0.0516
  -8.250  -0.5787   0.03220   0.02488  -0.0713   0.9250   0.0494
  -8.000  -0.5582   0.02999   0.02228  -0.0701   0.9211   0.0481
  -7.750  -0.5299   0.02823   0.02029  -0.0703   0.9187   0.0482
  -7.500  -0.5005   0.02701   0.01896  -0.0710   0.9168   0.0498
  -7.250  -0.4681   0.02577   0.01759  -0.0721   0.9153   0.0512
  -7.000  -0.4322   0.02450   0.01619  -0.0736   0.9142   0.0523
  -6.750  -0.4102   0.02383   0.01545  -0.0728   0.9106   0.0533
  -6.500  -0.3866   0.02326   0.01481  -0.0722   0.9075   0.0544
  -6.250  -0.3561   0.02202   0.01365  -0.0732   0.9057   0.0576
  -6.000  -0.3362   0.02148   0.01313  -0.0722   0.9030   0.0604
  -5.750  -0.3168   0.02098   0.01261  -0.0710   0.9006   0.0631
  -5.500  -0.2975   0.02058   0.01215  -0.0697   0.8984   0.0658
  -5.250  -0.3082   0.02081   0.01239  -0.0632   0.8916   0.0675
  -5.000  -0.3025   0.02055   0.01216  -0.0597   0.8880   0.0720
  -4.750  -0.2870   0.02030   0.01186  -0.0578   0.8857   0.0782
  -4.500  -0.2721   0.01985   0.01144  -0.0559   0.8838   0.0909
  -4.250  -0.2891   0.02029   0.01193  -0.0481   0.8774   0.0993
  -4.000  -0.3033   0.01984   0.01195  -0.0411   0.8728   0.1780
  -3.750  -0.3239   0.01811   0.01154  -0.0335   0.8694   0.4450
  -3.500  -0.3162   0.01811   0.01267  -0.0283   0.8677   0.7070
  -3.250  -0.3352   0.01884   0.01340  -0.0198   0.8626   0.7228
  -3.000  -0.3287   0.01948   0.01398  -0.0157   0.8593   0.7457
  -2.750  -0.3114   0.02037   0.01487  -0.0127   0.8570   0.7656
  -2.500  -0.2911   0.02150   0.01602  -0.0097   0.8550   0.7866
  -2.250  -0.2680   0.02278   0.01730  -0.0067   0.8533   0.8097
  -2.000  -0.2384   0.02404   0.01854  -0.0049   0.8522   0.8257
  -1.750  -0.1937   0.02542   0.01989  -0.0057   0.8516   0.8371
  -1.500  -0.2304   0.02548   0.01997   0.0051   0.8446   0.8446
  -1.250  -0.2187   0.02587   0.02031   0.0083   0.8413   0.8566
  -1.000  -0.1824   0.02639   0.02079   0.0074   0.8396   0.8611
  -0.750  -0.1486   0.02654   0.02088   0.0062   0.8377   0.8648
  -0.500  -0.1157   0.02649   0.02076   0.0048   0.8361   0.8684
  -0.250  -0.1370   0.02644   0.02070   0.0127   0.8290   0.8753
   0.000  -0.1154   0.02649   0.02072   0.0134   0.8252   0.8781
   0.250  -0.0844   0.02647   0.02066   0.0124   0.8226   0.8806
   0.500  -0.0494   0.02642   0.02057   0.0107   0.8206   0.8828
   0.750  -0.0086   0.02635   0.02047   0.0079   0.8192   0.8844
   1.000  -0.0328   0.02628   0.02040   0.0160   0.8088   0.8904
   1.250   0.0018   0.02623   0.02034   0.0144   0.8062   0.8915
   1.500   0.0412   0.02618   0.02028   0.0121   0.8044   0.8925
   1.750   0.0837   0.02616   0.02026   0.0092   0.8031   0.8935
   2.000   0.0701   0.02625   0.02036   0.0154   0.7917   0.8985
   2.250   0.1077   0.02614   0.02026   0.0134   0.7894   0.8998
   2.500   0.1409   0.02607   0.02021   0.0120   0.7862   0.9015
   2.750   0.1474   0.02611   0.02026   0.0149   0.7765   0.9051
   3.000   0.1874   0.02589   0.02009   0.0128   0.7741   0.9063
   3.250   0.2326   0.02559   0.01984   0.0099   0.7725   0.9070
   3.500   0.2350   0.02576   0.02005   0.0136   0.7609   0.9110
   3.750   0.2779   0.02537   0.01973   0.0111   0.7586   0.9120
   4.000   0.3132   0.02506   0.01948   0.0098   0.7544   0.9138
   4.250   0.3340   0.02482   0.01930   0.0108   0.7451   0.9171
   4.500   0.4298   0.02205   0.01667   0.0021   0.7435   0.9133
   4.750   0.5285   0.01875   0.01348  -0.0071   0.7341   0.9095
   5.000   0.5907   0.01639   0.01115  -0.0109   0.7140   0.9090
   5.250   0.6201   0.01546   0.01028  -0.0103   0.6946   0.9112
   5.500   0.6180   0.01510   0.01000  -0.0046   0.6699   0.9171
   5.750   0.6337   0.01414   0.00864  -0.0008   0.5560   0.9205
   6.000   0.6149   0.01467   0.00845   0.0080   0.4409   0.9270
   6.250   0.5898   0.01574   0.00893   0.0166   0.3349   0.9353
   6.500   0.5679   0.01728   0.00976   0.0236   0.2047   0.9443
   6.750   0.5587   0.01902   0.01078   0.0282   0.0936   0.9517
   7.000   0.5696   0.01992   0.01157   0.0300   0.0756   0.9587
   7.250   0.5895   0.02079   0.01248   0.0301   0.0669   0.9638
   7.500   0.6071   0.02192   0.01359   0.0303   0.0614   0.9695
   7.750   0.6323   0.02279   0.01452   0.0295   0.0575   0.9740
   8.000   0.6595   0.02377   0.01549   0.0282   0.0531   0.9777
   8.250   0.6873   0.02513   0.01677   0.0274   0.0503   0.9812
   8.500   0.7212   0.02601   0.01773   0.0258   0.0486   0.9845
   8.750   0.7591   0.02704   0.01881   0.0237   0.0463   0.9866
   9.000   0.7969   0.02813   0.01993   0.0215   0.0440   0.9890
   9.250   0.8445   0.02988   0.02165   0.0183   0.0422   0.9891
   9.500   0.9073   0.03368   0.02559   0.0131   0.0413   0.9849
   9.750   0.9447   0.03620   0.02838   0.0108   0.0411   0.9862
  10.000   0.9745   0.03857   0.03109   0.0093   0.0408   0.9893
  10.250   0.9989   0.04098   0.03385   0.0086   0.0405   0.9943
  10.500   1.0323   0.04602   0.03913   0.0064   0.0415   0.9960
  10.750   1.0292   0.04589   0.03920   0.0109   0.0421   1.0000
  12.500   0.7735   0.07888   0.07527   0.0422   0.0854   1.0000
  12.750   0.7397   0.08404   0.08055   0.0421   0.0854   1.0000
  13.000   0.7053   0.08999   0.08662   0.0409   0.0854   1.0000
  13.250   0.6663   0.09680   0.09354   0.0382   0.0854   1.0000
  13.500   0.6241   0.10481   0.10164   0.0336   0.0855   1.0000
<< Back to NACA 66(2)-215 (naca662215-il)

Polar data table (+)

Polar graphs


<< Back to NACA 66(2)-215 (naca662215-il)