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LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il)
Reynolds number: 50,000
Max Cl/Cd: 34.61 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141f-il-50000.txt
Download as CSV file: xf-c141f-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4335   0.10391   0.09649  -0.0187   1.0000   0.2549
  -7.750  -0.4242   0.10033   0.09297  -0.0169   1.0000   0.2657
  -7.500  -0.4548   0.10002   0.09283  -0.0150   1.0000   0.2752
  -7.250  -0.4402   0.09641   0.08925  -0.0127   1.0000   0.2921
  -7.000  -0.4350   0.09352   0.08642  -0.0102   1.0000   0.3085
  -6.750  -0.4364   0.09108   0.08406  -0.0074   1.0000   0.3254
  -6.500  -0.4399   0.08885   0.08193  -0.0042   1.0000   0.3441
  -6.250  -0.4436   0.08678   0.07993  -0.0007   1.0000   0.3654
  -6.000  -0.4564   0.08520   0.07848   0.0031   1.0000   0.3886
  -5.750  -0.4391   0.08235   0.07566   0.0071   1.0000   0.4228
  -5.500  -0.4350   0.08046   0.07385   0.0119   1.0000   0.4631
  -5.250  -0.4219   0.07871   0.07214   0.0176   1.0000   0.5222
  -5.000  -0.3182   0.07307   0.06630   0.0173   1.0000   0.6523
  -4.750  -0.2102   0.06645   0.05948   0.0115   1.0000   0.8085
  -4.000  -0.1075   0.05499   0.04800   0.0001   1.0000   0.9161
  -3.750  -0.1989   0.05750   0.05082   0.0169   1.0000   0.8352
  -3.500  -0.2800   0.05818   0.05179   0.0284   1.0000   0.7607
  -3.250  -0.3531   0.05857   0.05243   0.0401   1.0000   0.7348
  -3.000  -0.3294   0.04069   0.03161  -0.0258   1.0000   0.2106
  -2.750  -0.2993   0.03835   0.02871  -0.0265   1.0000   0.1948
  -2.500  -0.2687   0.03659   0.02626  -0.0269   1.0000   0.1824
  -2.250  -0.2421   0.03481   0.02422  -0.0268   1.0000   0.1801
  -2.000  -0.2154   0.03340   0.02253  -0.0267   1.0000   0.1799
  -1.750  -0.1888   0.03214   0.02101  -0.0264   1.0000   0.1793
  -1.500  -0.1625   0.03110   0.01972  -0.0260   1.0000   0.1804
  -1.250  -0.1366   0.03037   0.01871  -0.0255   1.0000   0.1838
  -1.000  -0.1110   0.02933   0.01766  -0.0251   1.0000   0.1877
  -0.750  -0.0863   0.02864   0.01697  -0.0244   1.0000   0.1943
  -0.500  -0.0610   0.02822   0.01641  -0.0237   1.0000   0.2026
  -0.250  -0.0347   0.02764   0.01592  -0.0234   1.0000   0.2135
   0.000  -0.0090   0.02719   0.01555  -0.0231   1.0000   0.2301
   0.250   0.0173   0.02675   0.01524  -0.0230   1.0000   0.2562
   0.500   0.0431   0.02398   0.01533  -0.0216   1.0000   0.8038
   0.750   0.0604   0.02405   0.01492  -0.0194   1.0000   1.0000
   1.000   0.0819   0.02456   0.01504  -0.0187   1.0000   1.0000
   1.250   0.1028   0.02510   0.01535  -0.0182   1.0000   1.0000
   1.500   0.1234   0.02569   0.01577  -0.0178   1.0000   1.0000
   1.750   0.1437   0.02632   0.01629  -0.0175   1.0000   1.0000
   2.000   0.1637   0.02700   0.01688  -0.0172   1.0000   1.0000
   2.250   0.1834   0.02773   0.01755  -0.0170   1.0000   1.0000
   2.500   0.2027   0.02852   0.01830  -0.0168   1.0000   1.0000
   2.750   0.2216   0.02937   0.01914  -0.0167   1.0000   1.0000
   3.000   0.2571   0.03060   0.02038  -0.0198   0.9930   1.0000
   3.250   0.3276   0.03213   0.02198  -0.0290   0.9644   1.0000
   3.500   0.3884   0.03308   0.02305  -0.0356   0.9362   1.0000
   3.750   0.4493   0.03350   0.02361  -0.0413   0.9060   1.0000
   4.000   0.5097   0.03318   0.02351  -0.0460   0.8729   1.0000
   4.250   0.5811   0.03166   0.02230  -0.0505   0.8352   1.0000
   4.500   0.6613   0.02769   0.01870  -0.0526   0.7825   1.0000
   4.750   0.7282   0.02324   0.01443  -0.0509   0.6915   1.0000
   5.000   0.7739   0.02236   0.01240  -0.0485   0.5101   1.0000
   5.250   0.7952   0.02393   0.01303  -0.0463   0.4240   1.0000
   5.500   0.8227   0.02563   0.01421  -0.0458   0.3661   1.0000
   5.750   0.8542   0.02739   0.01563  -0.0461   0.3245   1.0000
   6.000   0.8875   0.02924   0.01721  -0.0468   0.2965   1.0000
   6.250   0.9160   0.03097   0.01892  -0.0467   0.2767   1.0000
   6.500   0.9446   0.03282   0.02068  -0.0467   0.2617   1.0000
   6.750   0.9679   0.03452   0.02264  -0.0458   0.2496   1.0000
   7.000   0.9911   0.03652   0.02480  -0.0450   0.2395   1.0000
   7.250   1.0145   0.03847   0.02685  -0.0442   0.2301   1.0000
   7.500   1.0326   0.04074   0.02942  -0.0427   0.2219   1.0000
   7.750   1.0516   0.04284   0.03172  -0.0414   0.2134   1.0000
   8.000   1.0670   0.04542   0.03454  -0.0397   0.2061   1.0000
   8.250   1.0776   0.04786   0.03737  -0.0373   0.1984   1.0000
   8.500   1.0958   0.05054   0.04004  -0.0362   0.1906   1.0000
   8.750   1.0947   0.05374   0.04384  -0.0327   0.1854   1.0000
   9.000   1.1049   0.05645   0.04673  -0.0307   0.1787   1.0000
   9.250   1.1127   0.05998   0.05042  -0.0287   0.1735   1.0000
   9.500   1.0987   0.06426   0.05520  -0.0249   0.1716   1.0000
   9.750   1.0816   0.06883   0.06015  -0.0215   0.1705   1.0000
  10.000   1.0597   0.07376   0.06537  -0.0184   0.1705   1.0000
  10.250   1.0333   0.07891   0.07073  -0.0157   0.1715   1.0000
  10.500   1.0073   0.08441   0.07634  -0.0139   0.1729   1.0000
  10.750   0.9871   0.09045   0.08246  -0.0136   0.1742   1.0000
  11.000   0.9757   0.09679   0.08885  -0.0141   0.1752   1.0000
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