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NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il)
Reynolds number: 100,000
Max Cl/Cd: 41.13 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ls417mod-il-100000-n5.txt
Download as CSV file: xf-ls417mod-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.4620   0.13187   0.12596  -0.0313   1.0000   0.0373
 -13.500  -0.4705   0.12472   0.11883  -0.0347   1.0000   0.0378
 -13.250  -0.6861   0.07375   0.06701  -0.0669   1.0000   0.0349
 -12.750  -0.7251   0.06399   0.05689  -0.0704   1.0000   0.0351
 -12.500  -0.7327   0.06088   0.05369  -0.0706   1.0000   0.0353
 -12.250  -0.7408   0.05798   0.05069  -0.0704   1.0000   0.0356
 -12.000  -0.7500   0.05525   0.04783  -0.0696   1.0000   0.0359
 -11.750  -0.7598   0.05278   0.04523  -0.0681   1.0000   0.0362
 -11.500  -0.7709   0.05061   0.04293  -0.0657   1.0000   0.0364
 -11.250  -0.7841   0.04877   0.04097  -0.0624   1.0000   0.0367
 -11.000  -0.7946   0.04701   0.03907  -0.0591   1.0000   0.0369
 -10.750  -0.8008   0.04526   0.03716  -0.0561   1.0000   0.0372
 -10.500  -0.8048   0.04364   0.03537  -0.0529   1.0000   0.0376
 -10.250  -0.8068   0.04209   0.03364  -0.0498   1.0000   0.0380
 -10.000  -0.8062   0.04058   0.03192  -0.0468   1.0000   0.0385
  -9.750  -0.8031   0.03912   0.03020  -0.0440   1.0000   0.0391
  -9.500  -0.7825   0.03790   0.02900  -0.0441   0.9976   0.0399
  -9.250  -0.7544   0.03658   0.02761  -0.0456   0.9936   0.0412
  -9.000  -0.7268   0.03513   0.02596  -0.0467   0.9894   0.0429
  -8.750  -0.6987   0.03385   0.02459  -0.0477   0.9850   0.0442
  -8.500  -0.6691   0.03273   0.02346  -0.0489   0.9813   0.0455
  -8.250  -0.6408   0.03162   0.02227  -0.0497   0.9776   0.0470
  -8.000  -0.6145   0.03060   0.02117  -0.0500   0.9729   0.0486
  -7.750  -0.5861   0.02971   0.02032  -0.0511   0.9690   0.0507
  -7.500  -0.5551   0.02882   0.01935  -0.0523   0.9660   0.0535
  -7.250  -0.5305   0.02798   0.01857  -0.0526   0.9604   0.0557
  -7.000  -0.5002   0.02712   0.01765  -0.0537   0.9553   0.0586
  -6.750  -0.4644   0.02617   0.01675  -0.0561   0.9512   0.0625
  -6.500  -0.4355   0.02535   0.01595  -0.0570   0.9439   0.0674
  -6.250  -0.3999   0.02444   0.01507  -0.0592   0.9379   0.0744
  -6.000  -0.3609   0.02350   0.01417  -0.0619   0.9339   0.0854
  -5.750  -0.3349   0.02274   0.01353  -0.0622   0.9255   0.1002
  -5.500  -0.3012   0.02183   0.01282  -0.0640   0.9195   0.1284
  -5.250  -0.2642   0.02080   0.01210  -0.0665   0.9151   0.1783
  -5.000  -0.2397   0.01993   0.01162  -0.0668   0.9057   0.2446
  -4.750  -0.2059   0.01882   0.01105  -0.0690   0.8996   0.3476
  -4.500  -0.1737   0.01810   0.01099  -0.0699   0.8942   0.4599
  -4.250  -0.1540   0.01849   0.01182  -0.0667   0.8840   0.5364
  -4.000  -0.1198   0.01872   0.01204  -0.0669   0.8770   0.5894
  -3.750  -0.0924   0.01905   0.01231  -0.0659   0.8674   0.6161
  -3.500  -0.0610   0.01924   0.01239  -0.0656   0.8575   0.6363
  -3.250  -0.0308   0.01935   0.01237  -0.0654   0.8466   0.6532
  -3.000  -0.0048   0.01970   0.01267  -0.0637   0.8358   0.6653
  -2.750   0.0218   0.01998   0.01287  -0.0623   0.8254   0.6781
  -2.500   0.0486   0.02018   0.01299  -0.0611   0.8133   0.6904
  -2.250   0.0745   0.02027   0.01302  -0.0599   0.8004   0.6985
  -2.000   0.1016   0.02029   0.01295  -0.0587   0.7870   0.7044
  -1.750   0.1297   0.02017   0.01272  -0.0587   0.7695   0.7129
  -1.500   0.1564   0.02009   0.01255  -0.0580   0.7506   0.7190
  -1.250   0.1800   0.02011   0.01250  -0.0562   0.7282   0.7238
  -1.000   0.2062   0.02004   0.01231  -0.0554   0.6994   0.7302
  -0.750   0.2373   0.01986   0.01192  -0.0561   0.6555   0.7384
  -0.500   0.2598   0.01993   0.01169  -0.0540   0.5962   0.7421
  -0.250   0.2822   0.02017   0.01151  -0.0523   0.5425   0.7466
   0.000   0.3065   0.02043   0.01144  -0.0515   0.5083   0.7519
   0.250   0.3355   0.02064   0.01136  -0.0522   0.4848   0.7578
   0.500   0.3613   0.02081   0.01137  -0.0519   0.4678   0.7615
   0.750   0.3857   0.02100   0.01144  -0.0510   0.4546   0.7646
   1.000   0.4114   0.02120   0.01149  -0.0506   0.4429   0.7683
   1.250   0.4394   0.02135   0.01154  -0.0508   0.4326   0.7720
   1.500   0.4691   0.02151   0.01158  -0.0516   0.4228   0.7759
   1.750   0.5014   0.02170   0.01162  -0.0530   0.4143   0.7798
   2.000   0.5280   0.02182   0.01172  -0.0528   0.4061   0.7819
   2.250   0.5541   0.02200   0.01183  -0.0525   0.3987   0.7844
   2.500   0.5813   0.02223   0.01195  -0.0525   0.3921   0.7871
   2.750   0.6095   0.02238   0.01212  -0.0528   0.3850   0.7899
   3.000   0.6387   0.02257   0.01226  -0.0534   0.3782   0.7924
   3.250   0.6686   0.02285   0.01242  -0.0541   0.3723   0.7955
   3.500   0.6998   0.02307   0.01265  -0.0553   0.3658   0.7988
   3.750   0.7274   0.02327   0.01287  -0.0555   0.3596   0.8011
   4.000   0.7539   0.02349   0.01307  -0.0554   0.3541   0.8031
   4.250   0.7813   0.02380   0.01329  -0.0555   0.3491   0.8052
   4.500   0.8083   0.02402   0.01360  -0.0556   0.3433   0.8076
   4.750   0.8356   0.02428   0.01389  -0.0558   0.3376   0.8105
   5.000   0.8639   0.02458   0.01415  -0.0562   0.3325   0.8136
   5.250   0.8935   0.02494   0.01447  -0.0570   0.3278   0.8166
   5.500   0.9218   0.02525   0.01488  -0.0575   0.3221   0.8191
   5.750   0.9467   0.02553   0.01521  -0.0572   0.3169   0.8211
   6.000   0.9723   0.02582   0.01550  -0.0570   0.3123   0.8234
   6.250   0.9985   0.02620   0.01586  -0.0570   0.3080   0.8259
   6.500   1.0237   0.02656   0.01637  -0.0569   0.3025   0.8289
   6.750   1.0500   0.02693   0.01679  -0.0570   0.2974   0.8322
   7.000   1.0777   0.02731   0.01715  -0.0575   0.2929   0.8356
   7.250   1.1025   0.02772   0.01761  -0.0573   0.2884   0.8383
   7.500   1.1250   0.02813   0.01817  -0.0567   0.2832   0.8410
   7.750   1.1485   0.02851   0.01861  -0.0563   0.2783   0.8438
   8.000   1.1733   0.02889   0.01899  -0.0562   0.2742   0.8469
   8.250   1.1971   0.02941   0.01961  -0.0560   0.2694   0.8502
   8.500   1.2208   0.02994   0.02027  -0.0559   0.2641   0.8536
   8.750   1.2420   0.03034   0.02073  -0.0551   0.2596   0.8567
   9.000   1.2640   0.03073   0.02109  -0.0544   0.2559   0.8604
   9.250   1.2823   0.03136   0.02195  -0.0534   0.2507   0.8647
   9.500   1.3027   0.03193   0.02263  -0.0528   0.2457   0.8691
   9.750   1.3223   0.03236   0.02309  -0.0519   0.2416   0.8730
  10.000   1.3394   0.03295   0.02377  -0.0506   0.2373   0.8771
  10.250   1.3548   0.03366   0.02467  -0.0493   0.2323   0.8816
  10.500   1.3722   0.03426   0.02534  -0.0484   0.2278   0.8863
  10.750   1.3874   0.03471   0.02576  -0.0468   0.2244   0.8909
  11.000   1.3942   0.03563   0.02694  -0.0443   0.2196   0.8965
  11.250   1.4057   0.03646   0.02791  -0.0426   0.2151   0.9024
  11.500   1.4168   0.03709   0.02858  -0.0407   0.2114   0.9090
  11.750   1.4258   0.03810   0.02973  -0.0390   0.2073   0.9166
  12.000   1.4301   0.03922   0.03105  -0.0367   0.2029   0.9254
  12.250   1.4371   0.04017   0.03210  -0.0348   0.1991   0.9358
  12.500   1.4460   0.04102   0.03296  -0.0332   0.1957   0.9501
  12.750   1.4435   0.04270   0.03493  -0.0312   0.1914   1.0000
  13.000   1.4510   0.04443   0.03678  -0.0308   0.1871   1.0000
  13.250   1.4623   0.04584   0.03820  -0.0306   0.1835   1.0000
  13.500   1.4621   0.04840   0.04097  -0.0302   0.1793   1.0000
  13.750   1.4631   0.05088   0.04360  -0.0300   0.1752   1.0000
  14.000   1.4689   0.05288   0.04564  -0.0299   0.1718   1.0000
  14.250   1.4653   0.05598   0.04889  -0.0299   0.1682   1.0000
  14.500   1.4562   0.05980   0.05292  -0.0303   0.1644   1.0000
  14.750   1.4539   0.06293   0.05613  -0.0307   0.1610   1.0000
  15.000   1.4525   0.06604   0.05929  -0.0312   0.1580   1.0000
  15.250   1.4263   0.07266   0.06620  -0.0332   0.1546   1.0000
  15.500   1.4086   0.07852   0.07222  -0.0353   0.1512   1.0000
  15.750   1.4123   0.08133   0.07502  -0.0363   0.1482   1.0000
  16.000   1.3612   0.09313   0.08714  -0.0418   0.1448   1.0000
  16.250   1.2919   0.10884   0.10314  -0.0497   0.1403   1.0000
  16.500   1.3257   0.10659   0.10080  -0.0482   0.1379   1.0000
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