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NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il)
Reynolds number: 50,000
Max Cl/Cd: 29.7 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ls417-il-50000.txt
Download as CSV file: xf-ls417-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5855   0.09682   0.09002  -0.0483   1.0000   0.1537
  -9.750  -0.5515   0.09622   0.08947  -0.0446   1.0000   0.1568
  -9.500  -0.5953   0.08996   0.08325  -0.0448   1.0000   0.1485
  -9.250  -0.7146   0.08201   0.07511  -0.0431   1.0000   0.1378
  -9.000  -0.7266   0.07817   0.07121  -0.0415   1.0000   0.1359
  -8.750  -0.7449   0.07379   0.06668  -0.0401   1.0000   0.1337
  -8.500  -0.7641   0.06871   0.06128  -0.0392   1.0000   0.1309
  -8.250  -0.7774   0.06323   0.05522  -0.0389   1.0000   0.1281
  -8.000  -0.7743   0.05923   0.05078  -0.0386   1.0000   0.1277
  -7.750  -0.7639   0.05599   0.04722  -0.0382   1.0000   0.1285
  -7.500  -0.7500   0.05293   0.04383  -0.0381   1.0000   0.1295
  -7.250  -0.7331   0.05002   0.04056  -0.0380   1.0000   0.1305
  -7.000  -0.7137   0.04741   0.03759  -0.0379   1.0000   0.1321
  -6.750  -0.6926   0.04517   0.03497  -0.0378   1.0000   0.1354
  -6.500  -0.6701   0.04311   0.03248  -0.0378   1.0000   0.1401
  -6.250  -0.6493   0.04154   0.03101  -0.0371   1.0000   0.1462
  -6.000  -0.6257   0.04005   0.02916  -0.0366   1.0000   0.1534
  -5.750  -0.6049   0.03872   0.02801  -0.0356   1.0000   0.1635
  -5.500  -0.5835   0.03752   0.02689  -0.0343   1.0000   0.1770
  -5.250  -0.5624   0.03643   0.02595  -0.0329   1.0000   0.1972
  -5.000  -0.5416   0.03523   0.02505  -0.0316   1.0000   0.2294
  -4.750  -0.5181   0.03346   0.02400  -0.0316   1.0000   0.3004
  -4.500  -0.5096   0.03226   0.02512  -0.0259   1.0000   0.5101
  -4.000  -0.5049   0.03728   0.03017  -0.0081   1.0000   0.6655
  -3.750  -0.4987   0.03895   0.03168  -0.0013   1.0000   0.7013
  -3.500  -0.4961   0.04037   0.03300   0.0068   1.0000   0.7272
  -3.250  -0.4915   0.04145   0.03397   0.0138   1.0000   0.7594
  -3.000  -0.4870   0.04221   0.03462   0.0208   1.0000   0.7921
  -2.750  -0.4807   0.04255   0.03483   0.0271   1.0000   0.8242
  -2.500  -0.4685   0.04257   0.03470   0.0320   1.0000   0.8543
  -2.250  -0.4476   0.04246   0.03441   0.0346   1.0000   0.8859
  -2.000  -0.3881   0.04302   0.03468   0.0303   1.0000   0.9242
  -1.750  -0.2731   0.04440   0.03564   0.0137   1.0000   0.9583
  -1.500  -0.1975   0.04486   0.03584   0.0026   1.0000   0.9763
  -1.250  -0.1359   0.04526   0.03603  -0.0063   1.0000   0.9916
  -1.000  -0.0974   0.04545   0.03610  -0.0111   1.0000   1.0000
  -0.750  -0.0949   0.04519   0.03578  -0.0091   1.0000   1.0000
  -0.500  -0.0922   0.04496   0.03550  -0.0070   1.0000   1.0000
  -0.250  -0.0895   0.04477   0.03527  -0.0050   1.0000   1.0000
   0.000  -0.0868   0.04461   0.03506  -0.0029   1.0000   1.0000
   0.250  -0.0841   0.04446   0.03489  -0.0008   1.0000   1.0000
   0.500  -0.0815   0.04434   0.03474   0.0013   1.0000   1.0000
   0.750  -0.0789   0.04424   0.03462   0.0033   1.0000   1.0000
   1.000  -0.0763   0.04416   0.03452   0.0053   1.0000   1.0000
   1.250  -0.0737   0.04409   0.03445   0.0073   1.0000   1.0000
   1.500  -0.0709   0.04406   0.03440   0.0092   1.0000   1.0000
   1.750  -0.0678   0.04405   0.03440   0.0110   1.0000   1.0000
   2.000  -0.0644   0.04410   0.03445   0.0127   1.0000   1.0000
   2.250  -0.0587   0.04428   0.03464   0.0138   1.0000   1.0000
   2.500  -0.0497   0.04468   0.03505   0.0143   1.0000   1.0000
   2.750  -0.0374   0.04533   0.03571   0.0140   1.0000   1.0000
   3.000  -0.0225   0.04620   0.03660   0.0132   1.0000   1.0000
   3.250  -0.0058   0.04728   0.03770   0.0119   1.0000   1.0000
   3.500   0.0185   0.04888   0.03932   0.0091   0.9971   1.0000
   3.750   0.0779   0.05246   0.04293  -0.0002   0.9733   1.0000
   4.000   0.2338   0.05564   0.04604  -0.0188   0.8433   1.0000
   4.250   0.2837   0.05659   0.04702  -0.0228   0.8133   1.0000
   4.500   0.3186   0.05722   0.04771  -0.0248   0.7873   1.0000
   4.750   0.3627   0.05784   0.04840  -0.0278   0.7633   1.0000
   5.000   0.4137   0.05813   0.04877  -0.0312   0.7405   1.0000
   5.250   0.4515   0.05816   0.04889  -0.0326   0.7158   1.0000
   5.500   0.4874   0.05795   0.04877  -0.0336   0.6903   1.0000
   5.750   0.5382   0.05694   0.04787  -0.0354   0.6675   1.0000
   6.000   0.5928   0.05528   0.04634  -0.0370   0.6467   1.0000
   6.250   0.6272   0.05434   0.04553  -0.0370   0.6219   1.0000
   6.500   0.6721   0.05233   0.04366  -0.0371   0.5980   1.0000
   6.750   0.7333   0.04830   0.03981  -0.0370   0.5772   1.0000
   7.000   0.8057   0.04232   0.03399  -0.0365   0.5573   1.0000
   7.250   0.8763   0.03679   0.02848  -0.0360   0.5232   1.0000
   7.500   0.9473   0.03304   0.02425  -0.0367   0.4646   1.0000
   7.750   0.9846   0.03337   0.02406  -0.0370   0.4110   1.0000
   8.000   1.0235   0.03446   0.02472  -0.0383   0.3691   1.0000
   8.250   1.0560   0.03599   0.02604  -0.0395   0.3385   1.0000
   8.500   1.0923   0.03757   0.02743  -0.0412   0.3140   1.0000
   8.750   1.1263   0.03930   0.02908  -0.0427   0.2947   1.0000
   9.000   1.1563   0.04124   0.03105  -0.0439   0.2796   1.0000
   9.250   1.1888   0.04328   0.03306  -0.0454   0.2667   1.0000
   9.500   1.2195   0.04529   0.03508  -0.0467   0.2555   1.0000
   9.750   1.2361   0.04775   0.03782  -0.0463   0.2473   1.0000
  10.000   1.2615   0.04995   0.04011  -0.0469   0.2387   1.0000
  10.250   1.2789   0.05277   0.04311  -0.0468   0.2324   1.0000
  10.500   1.2782   0.05567   0.04641  -0.0445   0.2274   1.0000
  10.750   1.3002   0.05813   0.04893  -0.0449   0.2208   1.0000
  11.000   1.3115   0.06145   0.05241  -0.0443   0.2162   1.0000
  11.250   1.2878   0.06509   0.05649  -0.0401   0.2144   1.0000
  11.500   1.2577   0.06931   0.06107  -0.0361   0.2132   1.0000
  11.750   1.2192   0.07464   0.06674  -0.0329   0.2128   1.0000
  12.000   1.1687   0.08181   0.07422  -0.0310   0.2137   1.0000
  12.250   1.1079   0.09159   0.08425  -0.0313   0.2157   1.0000
  12.500   1.0514   0.10347   0.09626  -0.0343   0.2175   1.0000
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