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NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il)
Reynolds number: 200,000
Max Cl/Cd: 55.68 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf414f-il-200000.txt
Download as CSV file: xf-nlf414f-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY NLF 0414F 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2103   0.10264   0.09902  -0.0843   0.9147   0.0529
 -11.250  -0.2066   0.09907   0.09546  -0.0860   0.9149   0.0544
 -11.000  -0.3494   0.10059   0.09688  -0.0830   0.9132   0.0506
 -10.750  -0.3357   0.09860   0.09488  -0.0823   0.9133   0.0515
 -10.500  -0.3274   0.09553   0.09181  -0.0838   0.9134   0.0527
 -10.250  -0.3231   0.09158   0.08787  -0.0867   0.9135   0.0541
 -10.000  -0.3234   0.08643   0.08273  -0.0915   0.9136   0.0558
  -9.750  -0.3347   0.07859   0.07488  -0.1007   0.9133   0.0571
  -9.500  -0.3571   0.07216   0.06832  -0.1079   0.9130   0.0581
  -9.250  -0.3909   0.06915   0.06503  -0.1106   0.9131   0.0591
  -9.000  -0.4158   0.06826   0.06373  -0.1097   0.9132   0.0596
  -8.750  -0.4115   0.06185   0.05743  -0.1103   0.9128   0.0609
  -8.500  -0.6912   0.08865   0.08531  -0.0360   1.0000   0.0494
  -8.250  -0.7174   0.08541   0.08183  -0.0339   1.0000   0.0496
  -8.000  -0.7327   0.08242   0.07857  -0.0319   1.0000   0.0497
  -7.750  -0.7255   0.07567   0.07206  -0.0317   1.0000   0.0506
  -7.500  -0.7211   0.07282   0.06925  -0.0305   1.0000   0.0513
  -7.250  -0.7183   0.07011   0.06650  -0.0292   1.0000   0.0521
  -7.000  -0.7150   0.06735   0.06366  -0.0281   1.0000   0.0532
  -6.750  -0.7107   0.06436   0.06052  -0.0272   1.0000   0.0549
  -6.500  -0.7083   0.06028   0.05554  -0.0273   0.9993   0.0604
  -4.500  -0.4708   0.03312   0.02552  -0.0388   0.9739   0.0392
  -4.250  -0.4369   0.03160   0.02373  -0.0400   0.9726   0.0376
  -4.000  -0.4088   0.03036   0.02228  -0.0400   0.9661   0.0371
  -3.750  -0.3763   0.02959   0.02140  -0.0411   0.9626   0.0374
  -3.500  -0.3419   0.02916   0.02090  -0.0426   0.9603   0.0384
  -3.250  -0.3055   0.02929   0.02096  -0.0446   0.9587   0.0409
  -3.000  -0.2820   0.02826   0.02002  -0.0444   0.9493   0.0436
  -2.750  -0.2467   0.02812   0.01990  -0.0464   0.9467   0.0473
  -2.500  -0.2083   0.02802   0.01984  -0.0493   0.9450   0.0538
  -2.250  -0.1672   0.02819   0.02012  -0.0527   0.9439   0.0790
  -2.000  -0.1500   0.02597   0.02084  -0.0515   0.9346   0.7329
  -1.750  -0.1241   0.02791   0.02274  -0.0494   0.9304   0.7767
  -1.500  -0.1140   0.02840   0.02324  -0.0445   0.9184   0.7987
  -1.250  -0.0945   0.02973   0.02458  -0.0409   0.9151   0.8248
  -1.000  -0.0926   0.02969   0.02455  -0.0342   0.9027   0.8501
  -0.750  -0.0947   0.02978   0.02467  -0.0263   0.8927   0.8750
  -0.500  -0.0822   0.02997   0.02484  -0.0215   0.8869   0.8977
  -0.250  -0.0674   0.02993   0.02474  -0.0190   0.8762   0.9066
   0.000  -0.0267   0.03055   0.02525  -0.0219   0.8715   0.9094
   0.250  -0.0024   0.03043   0.02507  -0.0212   0.8586   0.9128
   0.500   0.0488   0.02987   0.02438  -0.0233   0.8307   0.9145
   0.750   0.0928   0.03012   0.02455  -0.0261   0.8261   0.9158
   1.000   0.1120   0.03001   0.02441  -0.0251   0.8152   0.9181
   1.250   0.1518   0.03020   0.02455  -0.0274   0.8115   0.9190
   1.500   0.1951   0.03058   0.02489  -0.0301   0.8089   0.9197
   1.750   0.2084   0.03038   0.02469  -0.0287   0.7977   0.9216
   2.000   0.2491   0.03057   0.02486  -0.0311   0.7951   0.9222
   2.250   0.2664   0.03066   0.02496  -0.0304   0.7849   0.9237
   2.500   0.3034   0.03074   0.02504  -0.0322   0.7813   0.9241
   2.750   0.3439   0.03083   0.02514  -0.0344   0.7792   0.9245
   3.000   0.3603   0.03096   0.02529  -0.0337   0.7686   0.9257
   3.250   0.3987   0.03086   0.02522  -0.0355   0.7653   0.9260
   3.500   0.4406   0.03071   0.02511  -0.0376   0.7634   0.9260
   3.750   0.4578   0.03072   0.02516  -0.0368   0.7522   0.9269
   4.000   0.5038   0.02993   0.02443  -0.0388   0.7493   0.9272
   4.250   0.5336   0.02911   0.02366  -0.0388   0.7383   0.9280
   4.500   0.5874   0.02730   0.02190  -0.0410   0.7349   0.9278
   4.750   0.6135   0.02677   0.02145  -0.0408   0.7243   0.9283
   5.000   0.6619   0.02507   0.01984  -0.0425   0.7211   0.9282
   5.250   0.6922   0.02396   0.01881  -0.0424   0.7090   0.9286
   5.500   0.7229   0.02292   0.01787  -0.0424   0.6965   0.9291
   5.750   0.7529   0.02193   0.01699  -0.0422   0.6827   0.9300
   6.000   0.7830   0.02090   0.01605  -0.0420   0.6656   0.9308
   6.250   0.8173   0.01961   0.01481  -0.0421   0.6351   0.9312
   6.500   0.8769   0.01575   0.00998  -0.0412   0.4802   0.9306
   6.750   0.8697   0.01773   0.01121  -0.0375   0.3592   0.9316
   7.000   0.8638   0.01985   0.01265  -0.0343   0.2480   0.9326
   7.250   0.8660   0.02160   0.01387  -0.0320   0.1710   0.9339
   7.500   0.8751   0.02300   0.01496  -0.0304   0.1276   0.9350
   7.750   0.8874   0.02426   0.01603  -0.0292   0.1035   0.9356
   8.000   0.9022   0.02537   0.01706  -0.0282   0.0900   0.9361
   8.250   0.9179   0.02643   0.01806  -0.0273   0.0814   0.9366
   8.500   0.9354   0.02738   0.01905  -0.0266   0.0754   0.9373
   8.750   0.9529   0.02832   0.01995  -0.0258   0.0703   0.9384
   9.000   0.9712   0.02936   0.02100  -0.0250   0.0662   0.9393
   9.250   0.9921   0.03021   0.02190  -0.0246   0.0630   0.9399
   9.500   1.0135   0.03110   0.02278  -0.0242   0.0602   0.9405
   9.750   1.0419   0.03227   0.02386  -0.0241   0.0572   0.9409
  10.000   1.0645   0.03309   0.02484  -0.0238   0.0553   0.9417
  10.250   1.0886   0.03402   0.02587  -0.0236   0.0532   0.9425
  10.500   1.1144   0.03506   0.02698  -0.0235   0.0515   0.9435
  10.750   1.1421   0.03622   0.02819  -0.0237   0.0500   0.9445
  11.000   1.1886   0.03867   0.03068  -0.0258   0.0480   0.9447
  11.250   1.2034   0.03996   0.03224  -0.0247   0.0472   0.9465
  11.500   1.2198   0.04160   0.03416  -0.0238   0.0462   0.9484
  11.750   1.2367   0.04368   0.03651  -0.0230   0.0454   0.9507
  12.000   1.2500   0.04604   0.03917  -0.0218   0.0449   0.9542
  12.250   1.2586   0.04867   0.04212  -0.0203   0.0445   0.9601
  12.500   1.2616   0.05157   0.04535  -0.0184   0.0444   0.9765
  12.750   1.2601   0.05487   0.04898  -0.0165   0.0443   1.0000
  13.000   1.2531   0.05842   0.05285  -0.0144   0.0442   1.0000
  13.250   1.2411   0.06224   0.05698  -0.0122   0.0443   1.0000
  13.500   1.2242   0.06643   0.06147  -0.0101   0.0444   1.0000
  13.750   1.2034   0.07106   0.06640  -0.0083   0.0446   1.0000
  14.000   1.1791   0.07617   0.07178  -0.0070   0.0449   1.0000
  14.250   1.1521   0.08180   0.07766  -0.0064   0.0453   1.0000
  14.500   1.1233   0.08800   0.08409  -0.0067   0.0458   1.0000
  14.750   1.0937   0.09486   0.09115  -0.0082   0.0463   1.0000
  15.000   1.0653   0.10239   0.09885  -0.0109   0.0468   1.0000
  15.250   1.0414   0.11035   0.10693  -0.0143   0.0474   1.0000
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