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

NACA 0008 (naca0008-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 0008 (naca0008-il)
Reynolds number: 500,000
Max Cl/Cd: 56.21 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0008-il-500000-n5.txt
Download as CSV file: xf-naca0008-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0008                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -1.0353   0.07502   0.07264   0.0049   1.0000   0.0050
 -13.000  -1.0853   0.05629   0.05354  -0.0104   1.0000   0.0048
 -12.750  -1.1054   0.04814   0.04513  -0.0176   1.0000   0.0048
 -12.500  -1.1217   0.04299   0.03975  -0.0202   1.0000   0.0048
 -12.250  -1.1347   0.03937   0.03591  -0.0196   1.0000   0.0048
 -12.000  -1.1413   0.03658   0.03291  -0.0177   1.0000   0.0049
 -11.750  -1.1383   0.03417   0.03029  -0.0164   1.0000   0.0050
 -11.500  -1.1301   0.03213   0.02804  -0.0152   1.0000   0.0051
 -11.250  -1.1185   0.03033   0.02605  -0.0141   1.0000   0.0052
 -11.000  -1.1046   0.02869   0.02422  -0.0131   1.0000   0.0054
 -10.750  -1.0892   0.02715   0.02249  -0.0122   1.0000   0.0056
 -10.500  -1.0725   0.02568   0.02083  -0.0112   1.0000   0.0058
 -10.250  -1.0545   0.02431   0.01926  -0.0104   1.0000   0.0060
 -10.000  -1.0351   0.02310   0.01787  -0.0096   1.0000   0.0063
  -9.750  -1.0146   0.02203   0.01658  -0.0088   1.0000   0.0067
  -9.500  -0.9937   0.02096   0.01535  -0.0081   1.0000   0.0069
  -9.250  -0.9743   0.01960   0.01384  -0.0072   1.0000   0.0074
  -9.000  -0.9522   0.01872   0.01284  -0.0066   1.0000   0.0078
  -8.750  -0.9293   0.01794   0.01196  -0.0060   1.0000   0.0083
  -8.500  -0.9062   0.01718   0.01109  -0.0055   1.0000   0.0088
  -8.250  -0.8828   0.01646   0.01026  -0.0049   1.0000   0.0094
  -8.000  -0.8589   0.01581   0.00950  -0.0043   1.0000   0.0099
  -7.750  -0.8357   0.01502   0.00861  -0.0037   1.0000   0.0113
  -7.500  -0.8111   0.01453   0.00811  -0.0033   1.0000   0.0126
  -7.250  -0.7863   0.01407   0.00759  -0.0029   1.0000   0.0140
  -7.000  -0.7617   0.01355   0.00700  -0.0024   1.0000   0.0155
  -6.750  -0.7366   0.01314   0.00660  -0.0019   1.0000   0.0183
  -6.500  -0.7110   0.01286   0.00629  -0.0016   1.0000   0.0212
  -6.250  -0.6852   0.01265   0.00602  -0.0012   1.0000   0.0229
  -6.000  -0.6607   0.01215   0.00547  -0.0007   1.0000   0.0255
  -5.750  -0.6356   0.01184   0.00515  -0.0003   1.0000   0.0280
  -5.500  -0.6103   0.01157   0.00484   0.0002   1.0000   0.0302
  -5.250  -0.5851   0.01131   0.00454   0.0007   1.0000   0.0318
  -5.000  -0.5599   0.01107   0.00425   0.0012   1.0000   0.0329
  -4.750  -0.5357   0.01065   0.00380   0.0019   1.0000   0.0361
  -4.500  -0.5111   0.01035   0.00350   0.0025   1.0000   0.0390
  -4.250  -0.4863   0.01010   0.00323   0.0031   1.0000   0.0418
  -4.000  -0.4614   0.00987   0.00296   0.0037   1.0000   0.0447
  -3.750  -0.4368   0.00960   0.00273   0.0043   1.0000   0.0521
  -3.500  -0.4124   0.00933   0.00253   0.0050   1.0000   0.0668
  -3.250  -0.3840   0.00901   0.00232   0.0047   0.9986   0.0932
  -3.000  -0.3498   0.00867   0.00212   0.0030   0.9950   0.1290
  -2.750  -0.3164   0.00832   0.00195   0.0016   0.9905   0.1722
  -2.500  -0.2821   0.00797   0.00179   0.0000   0.9860   0.2212
  -2.250  -0.2504   0.00758   0.00165  -0.0011   0.9789   0.2852
  -2.000  -0.2183   0.00721   0.00153  -0.0022   0.9712   0.3514
  -1.750  -0.1863   0.00684   0.00143  -0.0033   0.9618   0.4211
  -1.500  -0.1557   0.00649   0.00134  -0.0039   0.9494   0.4936
  -1.250  -0.1274   0.00614   0.00128  -0.0040   0.9333   0.5695
  -1.000  -0.1006   0.00587   0.00122  -0.0036   0.9136   0.6354
  -0.750  -0.0746   0.00570   0.00118  -0.0029   0.8907   0.6811
  -0.500  -0.0493   0.00559   0.00114  -0.0021   0.8635   0.7209
  -0.250  -0.0246   0.00552   0.00111  -0.0011   0.8318   0.7601
   0.000   0.0000   0.00550   0.00110   0.0000   0.7969   0.7968
   0.250   0.0246   0.00552   0.00111   0.0011   0.7602   0.8317
   0.500   0.0493   0.00559   0.00114   0.0021   0.7210   0.8634
   0.750   0.0745   0.00570   0.00118   0.0030   0.6807   0.8908
   1.000   0.1006   0.00586   0.00122   0.0036   0.6355   0.9138
   1.250   0.1274   0.00614   0.00128   0.0040   0.5701   0.9334
   1.500   0.1557   0.00649   0.00134   0.0039   0.4936   0.9494
   1.750   0.1863   0.00684   0.00143   0.0033   0.4212   0.9618
   2.000   0.2183   0.00721   0.00153   0.0022   0.3517   0.9712
   2.250   0.2504   0.00758   0.00165   0.0011   0.2852   0.9790
   2.500   0.2821   0.00797   0.00179   0.0000   0.2212   0.9860
   2.750   0.3165   0.00832   0.00195  -0.0016   0.1721   0.9905
   3.000   0.3498   0.00867   0.00212  -0.0031   0.1289   0.9950
   3.250   0.3841   0.00901   0.00232  -0.0047   0.0930   0.9986
   3.500   0.4124   0.00933   0.00253  -0.0050   0.0669   1.0000
   3.750   0.4369   0.00960   0.00273  -0.0044   0.0521   1.0000
   4.000   0.4615   0.00987   0.00296  -0.0037   0.0448   1.0000
   4.250   0.4863   0.01010   0.00323  -0.0031   0.0418   1.0000
   4.500   0.5111   0.01035   0.00350  -0.0025   0.0390   1.0000
   4.750   0.5357   0.01065   0.00380  -0.0019   0.0361   1.0000
   5.000   0.5600   0.01107   0.00425  -0.0012   0.0329   1.0000
   5.250   0.5851   0.01131   0.00453  -0.0007   0.0318   1.0000
   5.500   0.6103   0.01157   0.00484  -0.0002   0.0302   1.0000
   5.750   0.6356   0.01184   0.00515   0.0003   0.0280   1.0000
   6.000   0.6607   0.01215   0.00547   0.0007   0.0254   1.0000
   6.250   0.6852   0.01265   0.00602   0.0012   0.0229   1.0000
   6.500   0.7110   0.01286   0.00629   0.0016   0.0212   1.0000
   6.750   0.7366   0.01314   0.00660   0.0019   0.0183   1.0000
   7.000   0.7617   0.01355   0.00700   0.0024   0.0155   1.0000
   7.250   0.7862   0.01407   0.00759   0.0029   0.0140   1.0000
   7.500   0.8110   0.01453   0.00811   0.0033   0.0126   1.0000
   7.750   0.8357   0.01502   0.00861   0.0037   0.0113   1.0000
   8.000   0.8589   0.01581   0.00950   0.0044   0.0099   1.0000
   8.250   0.8827   0.01646   0.01026   0.0049   0.0094   1.0000
   8.500   0.9062   0.01718   0.01109   0.0055   0.0088   1.0000
   8.750   0.9293   0.01794   0.01196   0.0061   0.0083   1.0000
   9.000   0.9521   0.01872   0.01285   0.0066   0.0078   1.0000
   9.250   0.9743   0.01960   0.01384   0.0072   0.0074   1.0000
   9.500   0.9937   0.02096   0.01535   0.0081   0.0069   1.0000
   9.750   1.0146   0.02202   0.01658   0.0088   0.0067   1.0000
  10.000   1.0351   0.02310   0.01787   0.0096   0.0063   1.0000
  10.250   1.0545   0.02430   0.01925   0.0104   0.0060   1.0000
  10.500   1.0724   0.02568   0.02082   0.0112   0.0058   1.0000
  10.750   1.0892   0.02715   0.02249   0.0122   0.0056   1.0000
  11.000   1.1046   0.02869   0.02422   0.0131   0.0054   1.0000
  11.250   1.1185   0.03033   0.02605   0.0141   0.0052   1.0000
  11.500   1.1301   0.03212   0.02803   0.0152   0.0051   1.0000
  11.750   1.1384   0.03416   0.03027   0.0163   0.0050   1.0000
  12.000   1.1414   0.03659   0.03291   0.0177   0.0049   1.0000
  12.250   1.1350   0.03937   0.03591   0.0195   0.0048   1.0000
  12.500   1.1220   0.04300   0.03976   0.0201   0.0048   1.0000
  12.750   1.1055   0.04820   0.04519   0.0175   0.0048   1.0000
  13.000   1.0859   0.05633   0.05358   0.0102   0.0048   1.0000
  13.250   1.0390   0.07435   0.07196  -0.0046   0.0050   1.0000
<< Back to NACA 0008 (naca0008-il)

Polar data table (+)

Polar graphs


<< Back to NACA 0008 (naca0008-il)