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

lrn1007 (lrn1007-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: lrn1007 (lrn1007-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.32 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-lrn1007-il-1000000.txt
Download as CSV file: xf-lrn1007-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: lrn1007                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.500   0.1830   0.02725   0.02375  -0.0972   0.7864   0.0015
  -2.250   0.2122   0.02519   0.02156  -0.0978   0.7876   0.0019
  -2.000   0.2414   0.02331   0.01953  -0.0979   0.7871   0.0024
  -1.750   0.2714   0.02176   0.01785  -0.0978   0.7866   0.0031
  -1.500   0.3027   0.02093   0.01689  -0.0972   0.7860   0.0035
  -1.250   0.3320   0.01938   0.01519  -0.0970   0.7853   0.0036
  -1.000   0.3611   0.01782   0.01346  -0.0967   0.7843   0.0036
  -0.750   0.3897   0.01620   0.01168  -0.0964   0.7828   0.0036
  -0.500   0.4181   0.01464   0.00994  -0.0961   0.7807   0.0036
  -0.250   0.4465   0.01301   0.00813  -0.0956   0.7787   0.0037
   0.000   0.4743   0.01105   0.00593  -0.0951   0.7766   0.0044
   2.250   0.7177   0.00708   0.00154  -0.0947   0.7510   0.0130
   2.500   0.7450   0.00699   0.00140  -0.0948   0.7468   0.0113
   2.750   0.7703   0.00605   0.00121  -0.0947   0.7344   0.4914
   3.000   0.7720   0.00793   0.00156  -0.0905   0.3284   0.6260
   3.250   0.7740   0.00968   0.00254  -0.0867   0.0259   0.8419
   3.500   0.8106   0.00972   0.00275  -0.0889   0.0046   1.0000
   3.750   0.8363   0.00996   0.00307  -0.0885   0.0070   1.0000
   4.000   0.8626   0.01019   0.00349  -0.0879   0.0096   1.0000
   4.250   0.8856   0.01082   0.00427  -0.0868   0.0078   1.0000
   4.750   0.9232   0.01299   0.00665  -0.0835   0.0025   1.0000
   5.000   0.9411   0.01422   0.00792  -0.0817   0.0019   1.0000
   5.250   0.9575   0.01606   0.00979  -0.0797   0.0014   1.0000
   7.000   1.1020   0.03635   0.03177  -0.0685   0.0012   1.0000
   7.250   1.1136   0.03938   0.03513  -0.0657   0.0012   1.0000
   7.500   1.1273   0.04229   0.03840  -0.0629   0.0011   1.0000
   7.750   1.1346   0.04587   0.04225  -0.0600   0.0011   1.0000
   8.000   1.1387   0.04957   0.04619  -0.0571   0.0011   1.0000
   8.250   1.1396   0.05326   0.05011  -0.0540   0.0011   1.0000
   8.500   1.1369   0.05698   0.05403  -0.0509   0.0011   1.0000
   8.750   1.1309   0.06052   0.05775  -0.0478   0.0011   1.0000
   9.000   1.1181   0.06352   0.06090  -0.0439   0.0011   1.0000
   9.250   1.1018   0.06650   0.06401  -0.0404   0.0011   1.0000
   9.500   1.0855   0.06992   0.06755  -0.0382   0.0011   1.0000
   9.750   1.0684   0.07378   0.07153  -0.0369   0.0011   1.0000
  10.000   1.0513   0.07809   0.07595  -0.0365   0.0011   1.0000
  10.250   1.0343   0.08292   0.08089  -0.0371   0.0011   1.0000
<< Back to lrn1007 (lrn1007-il)

Polar data table (+)

Polar graphs


<< Back to lrn1007 (lrn1007-il)