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

LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)
Reynolds number: 100,000
Max Cl/Cd: 47.17 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141d-il-100000.txt
Download as CSV file: xf-c141d-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL610.61 AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4849   0.09822   0.09289  -0.0342   1.0000   0.1232
  -9.000  -0.5182   0.09448   0.08929  -0.0382   1.0000   0.1259
  -8.750  -0.5555   0.09115   0.08606  -0.0393   1.0000   0.1263
  -8.500  -0.5167   0.08767   0.08257  -0.0349   1.0000   0.1316
  -8.250  -0.5246   0.08499   0.07997  -0.0335   1.0000   0.1349
  -8.000  -0.5497   0.08207   0.07712  -0.0323   1.0000   0.1370
  -7.750  -0.5838   0.07876   0.07380  -0.0322   1.0000   0.1405
  -7.500  -0.6383   0.07758   0.07220  -0.0307   1.0000   0.1427
  -7.250  -0.5979   0.07194   0.06701  -0.0284   1.0000   0.1473
  -7.000  -0.5985   0.06934   0.06441  -0.0263   1.0000   0.1522
  -6.750  -0.6216   0.06575   0.06057  -0.0254   1.0000   0.1610
  -6.500  -0.6097   0.06290   0.05783  -0.0230   1.0000   0.1648
  -6.250  -0.6317   0.04684   0.03966  -0.0224   1.0000   0.0857
  -6.000  -0.6159   0.04310   0.03599  -0.0213   1.0000   0.0827
  -5.750  -0.6035   0.03928   0.03179  -0.0195   1.0000   0.0799
  -5.500  -0.5883   0.03635   0.02841  -0.0178   1.0000   0.0806
  -5.250  -0.5704   0.03379   0.02537  -0.0162   1.0000   0.0822
  -5.000  -0.5501   0.03138   0.02245  -0.0148   1.0000   0.0836
  -4.750  -0.5282   0.02913   0.01978  -0.0138   1.0000   0.0870
  -4.500  -0.5060   0.02788   0.01853  -0.0131   1.0000   0.0928
  -4.250  -0.4825   0.02677   0.01695  -0.0120   1.0000   0.0987
  -4.000  -0.4590   0.02524   0.01550  -0.0116   1.0000   0.1059
  -3.750  -0.4349   0.02424   0.01426  -0.0109   1.0000   0.1138
  -3.500  -0.4115   0.02333   0.01341  -0.0103   1.0000   0.1224
  -3.250  -0.3874   0.02241   0.01247  -0.0097   1.0000   0.1310
  -3.000  -0.3639   0.02185   0.01184  -0.0090   1.0000   0.1417
  -2.750  -0.3402   0.02102   0.01118  -0.0084   1.0000   0.1539
  -2.500  -0.3167   0.02035   0.01063  -0.0079   1.0000   0.1696
  -2.250  -0.2932   0.01975   0.01016  -0.0073   1.0000   0.1931
  -2.000  -0.2690   0.01893   0.00974  -0.0071   1.0000   0.2432
  -1.750  -0.2536   0.01659   0.01030  -0.0021   1.0000   0.8373
  -1.500  -0.1633   0.01750   0.01102  -0.0126   1.0000   1.0000
  -1.250  -0.1559   0.01745   0.01083  -0.0098   1.0000   1.0000
  -1.000  -0.1446   0.01751   0.01073  -0.0077   1.0000   1.0000
  -0.750  -0.1302   0.01765   0.01072  -0.0061   1.0000   1.0000
  -0.500  -0.1138   0.01785   0.01079  -0.0048   1.0000   1.0000
  -0.250  -0.0962   0.01811   0.01093  -0.0038   1.0000   1.0000
   0.000  -0.0779   0.01841   0.01113  -0.0030   1.0000   1.0000
   0.250  -0.0414   0.01896   0.01156  -0.0056   0.9953   1.0000
   0.500  -0.0003   0.01953   0.01205  -0.0092   0.9879   1.0000
   0.750   0.0403   0.02011   0.01256  -0.0125   0.9802   1.0000
   1.000   0.0829   0.02072   0.01311  -0.0162   0.9729   1.0000
   1.250   0.1179   0.02115   0.01351  -0.0184   0.9632   1.0000
   1.500   0.1564   0.02163   0.01398  -0.0211   0.9541   1.0000
   1.750   0.2017   0.02211   0.01446  -0.0250   0.9454   1.0000
   2.000   0.2390   0.02237   0.01475  -0.0273   0.9329   1.0000
   2.250   0.2810   0.02254   0.01495  -0.0301   0.9195   1.0000
   2.500   0.3325   0.02236   0.01485  -0.0341   0.9035   1.0000
   2.750   0.3844   0.02196   0.01453  -0.0378   0.8877   1.0000
   3.000   0.4544   0.02072   0.01344  -0.0438   0.8696   1.0000
   3.250   0.5194   0.01934   0.01223  -0.0487   0.8530   1.0000
   3.500   0.5672   0.01825   0.01130  -0.0506   0.8367   1.0000
   3.750   0.6117   0.01713   0.01033  -0.0518   0.8174   1.0000
   4.000   0.6408   0.01636   0.00967  -0.0503   0.7899   1.0000
   4.250   0.6744   0.01550   0.00888  -0.0493   0.7520   1.0000
   4.500   0.7033   0.01491   0.00820  -0.0474   0.6810   1.0000
   4.750   0.7211   0.01545   0.00761  -0.0433   0.4598   1.0000
   5.000   0.7166   0.01746   0.00831  -0.0372   0.2917   1.0000
   5.250   0.7265   0.01885   0.00916  -0.0340   0.2338   1.0000
   5.500   0.7425   0.01998   0.00999  -0.0319   0.2055   1.0000
   5.750   0.7622   0.02099   0.01084  -0.0304   0.1858   1.0000
   6.000   0.7839   0.02200   0.01175  -0.0292   0.1703   1.0000
   6.250   0.8072   0.02309   0.01273  -0.0285   0.1575   1.0000
   6.500   0.8324   0.02435   0.01380  -0.0282   0.1459   1.0000
   6.750   0.8552   0.02526   0.01485  -0.0271   0.1357   1.0000
   7.000   0.8807   0.02664   0.01624  -0.0268   0.1266   1.0000
   7.250   0.9059   0.02800   0.01751  -0.0265   0.1183   1.0000
   7.500   0.9291   0.02947   0.01922  -0.0255   0.1108   1.0000
   7.750   0.9539   0.03111   0.02078  -0.0253   0.1042   1.0000
   8.000   0.9736   0.03283   0.02287  -0.0237   0.0985   1.0000
   8.250   0.9951   0.03442   0.02456  -0.0227   0.0934   1.0000
   8.500   1.0148   0.03687   0.02715  -0.0218   0.0891   1.0000
   8.750   1.0279   0.03889   0.02967  -0.0192   0.0856   1.0000
   9.000   1.0423   0.04125   0.03236  -0.0172   0.0829   1.0000
   9.250   1.0621   0.04325   0.03434  -0.0165   0.0798   1.0000
   9.500   1.0708   0.04663   0.03801  -0.0143   0.0776   1.0000
   9.750   1.0710   0.04964   0.04157  -0.0105   0.0765   1.0000
  10.000   1.0696   0.05330   0.04567  -0.0071   0.0762   1.0000
  10.250   1.0652   0.05722   0.04997  -0.0037   0.0763   1.0000
  10.500   1.0581   0.06130   0.05437  -0.0005   0.0766   1.0000
  10.750   1.0486   0.06545   0.05878   0.0025   0.0770   1.0000
  11.000   1.0380   0.06968   0.06322   0.0053   0.0775   1.0000
  11.250   1.0276   0.07407   0.06774   0.0077   0.0779   1.0000
  11.500   0.8344   0.11516   0.10985  -0.0045   0.1614   1.0000
<< Back to LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)

Polar data table (+)

Polar graphs


<< Back to LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)