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LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il)
Reynolds number: 100,000
Max Cl/Cd: 50.86 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141f-il-100000.txt
Download as CSV file: xf-c141f-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL958.89 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4518   0.10119   0.09583  -0.0307   1.0000   0.1036
  -8.250  -0.4848   0.09961   0.09438  -0.0313   1.0000   0.1043
  -8.000  -0.5195   0.09725   0.09201  -0.0345   1.0000   0.1048
  -7.750  -0.5054   0.09217   0.08703  -0.0313   1.0000   0.1061
  -7.500  -0.4880   0.08943   0.08435  -0.0267   1.0000   0.1081
  -7.250  -0.4877   0.08680   0.08175  -0.0250   1.0000   0.1103
  -7.000  -0.4930   0.08392   0.07890  -0.0246   1.0000   0.1129
  -6.750  -0.5037   0.08070   0.07566  -0.0262   1.0000   0.1167
  -6.500  -0.5242   0.07688   0.07157  -0.0302   1.0000   0.1201
  -6.250  -0.5122   0.07331   0.06820  -0.0269   1.0000   0.1220
  -6.000  -0.5050   0.07090   0.06584  -0.0245   1.0000   0.1254
  -5.750  -0.5102   0.06868   0.06308  -0.0282   1.0000   0.1353
  -5.500  -0.4995   0.06423   0.05889  -0.0258   1.0000   0.1373
  -5.250  -0.4897   0.06167   0.05640  -0.0239   1.0000   0.1408
  -5.000  -0.4813   0.05893   0.05327  -0.0256   1.0000   0.1522
  -4.750  -0.4698   0.05584   0.05033  -0.0237   1.0000   0.1553
  -4.500  -0.4568   0.05360   0.04780  -0.0243   1.0000   0.1690
  -4.250  -0.4436   0.05082   0.04516  -0.0227   1.0000   0.1737
  -4.000  -0.4293   0.04851   0.04275  -0.0224   1.0000   0.1892
  -3.750  -0.4144   0.04644   0.04063  -0.0217   1.0000   0.2070
  -3.500  -0.3989   0.04443   0.03862  -0.0209   1.0000   0.2264
  -3.250  -0.3825   0.04258   0.03677  -0.0200   1.0000   0.2486
  -3.000  -0.3671   0.04076   0.03497  -0.0190   1.0000   0.2822
  -2.750  -0.3501   0.03919   0.03339  -0.0180   1.0000   0.3178
  -2.500  -0.2728   0.03313   0.02498  -0.0244   1.0000   0.1325
  -2.250  -0.2435   0.03071   0.02207  -0.0241   1.0000   0.1161
  -2.000  -0.2180   0.02923   0.02034  -0.0238   1.0000   0.1139
  -1.750  -0.1928   0.02815   0.01903  -0.0234   1.0000   0.1139
  -1.500  -0.1675   0.02716   0.01783  -0.0230   1.0000   0.1133
  -1.250  -0.1425   0.02638   0.01688  -0.0226   1.0000   0.1137
  -1.000  -0.1183   0.02590   0.01625  -0.0221   1.0000   0.1167
  -0.750  -0.0943   0.02559   0.01578  -0.0215   1.0000   0.1191
  -0.500  -0.0689   0.02480   0.01505  -0.0215   1.0000   0.1221
  -0.250  -0.0449   0.02448   0.01481  -0.0213   1.0000   0.1278
   0.000  -0.0003   0.02440   0.01470  -0.0246   0.9950   0.1353
   0.250   0.0404   0.02403   0.01457  -0.0275   0.9894   0.1477
   0.750   0.1356   0.02302   0.01445  -0.0359   0.9754   0.2894
   1.000   0.1775   0.02145   0.01465  -0.0370   0.9637   1.0000
   1.250   0.2308   0.02173   0.01473  -0.0417   0.9484   1.0000
   1.500   0.2834   0.02176   0.01466  -0.0461   0.9326   1.0000
   1.750   0.3303   0.02165   0.01449  -0.0493   0.9176   1.0000
   2.000   0.3715   0.02160   0.01442  -0.0515   0.9055   1.0000
   2.250   0.4223   0.02138   0.01420  -0.0553   0.8966   1.0000
   2.500   0.4576   0.02114   0.01399  -0.0561   0.8830   1.0000
   2.750   0.4954   0.02077   0.01367  -0.0573   0.8696   1.0000
   3.000   0.5402   0.01994   0.01292  -0.0590   0.8543   1.0000
   3.250   0.5980   0.01813   0.01121  -0.0617   0.8356   1.0000
   3.500   0.6405   0.01670   0.00984  -0.0618   0.8095   1.0000
   3.750   0.6803   0.01567   0.00886  -0.0619   0.7785   1.0000
   4.000   0.7144   0.01499   0.00813  -0.0611   0.7274   1.0000
   4.250   0.7472   0.01469   0.00741  -0.0599   0.6092   1.0000
   4.500   0.7606   0.01584   0.00738  -0.0561   0.4296   1.0000
   4.750   0.7729   0.01712   0.00796  -0.0532   0.3515   1.0000
   5.000   0.7902   0.01817   0.00865  -0.0512   0.3067   1.0000
   5.250   0.8092   0.01924   0.00941  -0.0496   0.2715   1.0000
   5.500   0.8298   0.02039   0.01024  -0.0483   0.2425   1.0000
   5.750   0.8527   0.02145   0.01115  -0.0474   0.2197   1.0000
   6.000   0.8775   0.02253   0.01211  -0.0468   0.2039   1.0000
   6.250   0.9040   0.02370   0.01307  -0.0466   0.1917   1.0000
   6.500   0.9287   0.02455   0.01404  -0.0459   0.1818   1.0000
   6.750   0.9561   0.02578   0.01515  -0.0459   0.1739   1.0000
   7.000   0.9801   0.02665   0.01619  -0.0451   0.1662   1.0000
   7.250   1.0071   0.02794   0.01729  -0.0452   0.1592   1.0000
   7.500   1.0286   0.02876   0.01840  -0.0439   0.1521   1.0000
   7.750   1.0533   0.02982   0.01930  -0.0436   0.1452   1.0000
   8.000   1.0734   0.03082   0.02059  -0.0422   0.1382   1.0000
   8.250   1.0970   0.03184   0.02149  -0.0417   0.1317   1.0000
   8.500   1.1157   0.03310   0.02307  -0.0401   0.1249   1.0000
   8.750   1.1392   0.03430   0.02410  -0.0398   0.1186   1.0000
   9.000   1.1544   0.03573   0.02594  -0.0376   0.1120   1.0000
   9.250   1.1773   0.03728   0.02732  -0.0373   0.1061   1.0000
   9.500   1.1884   0.03898   0.02951  -0.0345   0.1002   1.0000
   9.750   1.2119   0.04081   0.03111  -0.0345   0.0951   1.0000
  10.000   1.2149   0.04310   0.03408  -0.0306   0.0909   1.0000
  10.250   1.2326   0.04470   0.03570  -0.0295   0.0868   1.0000
  10.500   1.2421   0.04759   0.03880  -0.0274   0.0840   1.0000
  10.750   1.2353   0.05082   0.04264  -0.0230   0.0817   1.0000
  11.000   1.2324   0.05372   0.04589  -0.0196   0.0795   1.0000
  11.250   1.2546   0.05504   0.04706  -0.0193   0.0765   1.0000
  11.500   1.2551   0.05869   0.05088  -0.0169   0.0752   1.0000
  11.750   1.2345   0.06247   0.05511  -0.0121   0.0749   1.0000
  12.000   1.2103   0.06615   0.05912  -0.0073   0.0748   1.0000
  12.250   1.1848   0.07021   0.06346  -0.0035   0.0748   1.0000
  12.500   1.1583   0.07474   0.06823  -0.0009   0.0749   1.0000
  12.750   1.1318   0.07984   0.07353   0.0003   0.0751   1.0000
  13.000   1.1069   0.08552   0.07938   0.0003   0.0754   1.0000
  13.250   0.9533   0.11525   0.10962  -0.0178   0.0848   1.0000
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