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LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il)
Reynolds number: 200,000
Max Cl/Cd: 63.07 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141b-il-200000.txt
Download as CSV file: xf-c141b-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL113.6 AIRFOIL                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6924   0.07736   0.07311  -0.0686   1.0000   0.0464
 -12.250  -0.7054   0.07239   0.06813  -0.0694   1.0000   0.0461
 -12.000  -0.7283   0.06756   0.06325  -0.0701   1.0000   0.0457
 -11.750  -0.7552   0.06346   0.05907  -0.0692   1.0000   0.0454
 -11.500  -0.7840   0.06025   0.05577  -0.0663   1.0000   0.0451
 -11.250  -0.8146   0.05787   0.05330  -0.0613   1.0000   0.0449
 -11.000  -0.8463   0.05618   0.05153  -0.0544   1.0000   0.0447
 -10.750  -0.8745   0.05387   0.04908  -0.0480   1.0000   0.0445
 -10.500  -0.8986   0.05105   0.04605  -0.0421   1.0000   0.0443
 -10.250  -0.9183   0.04801   0.04274  -0.0366   1.0000   0.0443
 -10.000  -0.9325   0.04485   0.03926  -0.0315   1.0000   0.0443
  -9.750  -0.9412   0.04177   0.03582  -0.0269   1.0000   0.0444
  -9.500  -0.9445   0.03893   0.03258  -0.0227   1.0000   0.0448
  -9.250  -0.9427   0.03640   0.02964  -0.0191   1.0000   0.0455
  -9.000  -0.9374   0.03443   0.02722  -0.0157   1.0000   0.0462
  -8.750  -0.9256   0.03213   0.02479  -0.0138   1.0000   0.0476
  -8.500  -0.9101   0.03121   0.02385  -0.0122   1.0000   0.0491
  -8.250  -0.8942   0.03017   0.02270  -0.0104   1.0000   0.0508
  -8.000  -0.8783   0.02885   0.02111  -0.0085   1.0000   0.0526
  -7.750  -0.8617   0.02781   0.01972  -0.0066   1.0000   0.0542
  -7.500  -0.8422   0.02613   0.01806  -0.0056   1.0000   0.0564
  -7.250  -0.8234   0.02549   0.01739  -0.0043   1.0000   0.0589
  -7.000  -0.8039   0.02479   0.01652  -0.0029   1.0000   0.0618
  -6.750  -0.7837   0.02365   0.01526  -0.0018   1.0000   0.0645
  -6.500  -0.7638   0.02296   0.01462  -0.0007   1.0000   0.0676
  -6.250  -0.7435   0.02244   0.01402   0.0005   1.0000   0.0713
  -6.000  -0.7228   0.02164   0.01312   0.0016   1.0000   0.0748
  -5.750  -0.7026   0.02102   0.01257   0.0026   1.0000   0.0790
  -5.500  -0.6810   0.02061   0.01209   0.0036   0.9999   0.0837
  -5.250  -0.6482   0.01989   0.01142   0.0021   0.9973   0.0898
  -5.000  -0.6134   0.01964   0.01110   0.0004   0.9947   0.0973
  -4.750  -0.5820   0.01902   0.01059  -0.0009   0.9917   0.1060
  -4.500  -0.5503   0.01856   0.01018  -0.0021   0.9882   0.1170
  -4.250  -0.5166   0.01817   0.00987  -0.0037   0.9853   0.1323
  -4.000  -0.4830   0.01782   0.00961  -0.0054   0.9823   0.1550
  -3.750  -0.4549   0.01726   0.00928  -0.0059   0.9779   0.1900
  -3.500  -0.4239   0.01652   0.00901  -0.0074   0.9745   0.2704
  -3.250  -0.3936   0.01541   0.00892  -0.0089   0.9721   0.4660
  -3.000  -0.3698   0.01490   0.00905  -0.0081   0.9674   0.6096
  -2.750  -0.3411   0.01483   0.00923  -0.0081   0.9627   0.6861
  -2.500  -0.3066   0.01494   0.00944  -0.0092   0.9592   0.7369
  -2.250  -0.2774   0.01503   0.00961  -0.0092   0.9548   0.7728
  -2.000  -0.2511   0.01509   0.00974  -0.0085   0.9488   0.8023
  -1.750  -0.2174   0.01525   0.00995  -0.0093   0.9451   0.8298
  -1.500  -0.1819   0.01548   0.01019  -0.0104   0.9420   0.8548
  -1.250  -0.1629   0.01555   0.01028  -0.0083   0.9340   0.8764
  -1.000  -0.1281   0.01577   0.01051  -0.0091   0.9301   0.8959
  -0.750  -0.0882   0.01606   0.01078  -0.0109   0.9277   0.9138
  -0.500  -0.0610   0.01637   0.01109  -0.0103   0.9206   0.9336
  -0.250  -0.0106   0.01685   0.01155  -0.0142   0.9181   0.9502
   0.000   0.0415   0.01707   0.01175  -0.0191   0.9158   0.9584
   0.250   0.0978   0.01718   0.01184  -0.0251   0.9141   0.9613
   0.500   0.1532   0.01720   0.01185  -0.0308   0.9126   0.9646
   0.750   0.1938   0.01724   0.01190  -0.0338   0.9065   0.9716
   1.000   0.2457   0.01715   0.01183  -0.0388   0.9023   0.9745
   1.250   0.3072   0.01668   0.01139  -0.0453   0.8989   0.9751
   1.500   0.3686   0.01567   0.01041  -0.0509   0.8903   0.9748
   1.750   0.4230   0.01483   0.00960  -0.0554   0.8829   0.9764
   2.000   0.4676   0.01426   0.00908  -0.0582   0.8739   0.9807
   2.250   0.5140   0.01358   0.00845  -0.0613   0.8652   0.9841
   2.500   0.5566   0.01303   0.00796  -0.0639   0.8515   0.9882
   2.750   0.5968   0.01252   0.00750  -0.0660   0.8350   0.9933
   3.000   0.6384   0.01200   0.00701  -0.0683   0.8129   0.9974
   3.250   0.6700   0.01161   0.00663  -0.0688   0.7820   1.0000
   3.500   0.6908   0.01136   0.00628  -0.0670   0.7406   1.0000
   3.750   0.7127   0.01130   0.00596  -0.0653   0.6814   1.0000
   4.000   0.7275   0.01160   0.00587  -0.0625   0.6004   1.0000
   4.250   0.7332   0.01226   0.00598  -0.0581   0.4940   1.0000
   4.500   0.7318   0.01321   0.00628  -0.0527   0.3774   1.0000
   4.750   0.7319   0.01415   0.00668  -0.0478   0.2851   1.0000
   5.000   0.7359   0.01495   0.00710  -0.0436   0.2254   1.0000
   5.250   0.7433   0.01560   0.00751  -0.0399   0.1871   1.0000
   5.500   0.7511   0.01624   0.00794  -0.0363   0.1622   1.0000
   5.750   0.7613   0.01678   0.00839  -0.0330   0.1438   1.0000
   6.000   0.7716   0.01736   0.00887  -0.0298   0.1298   1.0000
   6.250   0.7825   0.01795   0.00937  -0.0267   0.1186   1.0000
   6.500   0.7961   0.01844   0.00987  -0.0240   0.1092   1.0000
   6.750   0.8083   0.01914   0.01050  -0.0212   0.1015   1.0000
   7.000   0.8230   0.01965   0.01101  -0.0188   0.0946   1.0000
   7.250   0.8378   0.02046   0.01177  -0.0165   0.0887   1.0000
   7.500   0.8542   0.02100   0.01234  -0.0145   0.0831   1.0000
   7.750   0.8727   0.02205   0.01328  -0.0131   0.0781   1.0000
   8.000   0.8905   0.02259   0.01394  -0.0113   0.0738   1.0000
   8.250   0.9088   0.02331   0.01461  -0.0098   0.0699   1.0000
   8.500   0.9320   0.02449   0.01582  -0.0093   0.0661   1.0000
   8.750   0.9509   0.02521   0.01663  -0.0078   0.0627   1.0000
   9.000   0.9711   0.02608   0.01745  -0.0068   0.0598   1.0000
   9.250   0.9971   0.02767   0.01912  -0.0068   0.0571   1.0000
   9.500   1.0161   0.02865   0.02028  -0.0054   0.0547   1.0000
   9.750   1.0342   0.02958   0.02127  -0.0041   0.0524   1.0000
  10.000   1.0582   0.03106   0.02268  -0.0040   0.0502   1.0000
  10.250   1.0755   0.03278   0.02467  -0.0026   0.0488   1.0000
  10.500   1.0897   0.03437   0.02654  -0.0006   0.0474   1.0000
  10.750   1.1033   0.03608   0.02848   0.0014   0.0462   1.0000
  11.000   1.1167   0.03759   0.03013   0.0032   0.0450   1.0000
  11.250   1.1295   0.03896   0.03158   0.0049   0.0439   1.0000
  11.500   1.1459   0.04124   0.03388   0.0056   0.0428   1.0000
  11.750   1.1434   0.04366   0.03663   0.0095   0.0422   1.0000
  12.000   1.1352   0.04578   0.03910   0.0141   0.0418   1.0000
  12.250   1.1253   0.04840   0.04204   0.0183   0.0415   1.0000
  12.500   1.1117   0.05134   0.04528   0.0223   0.0413   1.0000
  12.750   1.0948   0.05459   0.04883   0.0259   0.0412   1.0000
  13.000   1.0747   0.05822   0.05274   0.0290   0.0412   1.0000
  13.250   1.0521   0.06229   0.05706   0.0313   0.0413   1.0000
  13.500   1.0274   0.06690   0.06191   0.0326   0.0414   1.0000
  13.750   1.0015   0.07211   0.06733   0.0326   0.0416   1.0000
  14.000   0.9743   0.07810   0.07350   0.0314   0.0418   1.0000
  14.250   0.9476   0.08482   0.08038   0.0289   0.0421   1.0000
  14.500   0.9237   0.09212   0.08779   0.0256   0.0424   1.0000
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