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RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG 14 10% AIRFOIL (rg1410-il)
Reynolds number: 200,000
Max Cl/Cd: 63.53 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg1410-il-200000.txt
Download as CSV file: xf-rg1410-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 10% 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5151   0.09986   0.09617  -0.0290   1.0000   0.0630
 -10.000  -0.5319   0.09345   0.08984  -0.0361   1.0000   0.0635
  -9.750  -0.5507   0.08641   0.08282  -0.0432   1.0000   0.0636
  -9.500  -0.5257   0.08546   0.08189  -0.0333   1.0000   0.0656
  -9.250  -0.5210   0.08277   0.07922  -0.0327   1.0000   0.0669
  -9.000  -0.5237   0.07904   0.07553  -0.0340   1.0000   0.0681
  -8.750  -0.5365   0.07405   0.07060  -0.0374   1.0000   0.0689
  -8.500  -0.5584   0.06940   0.06596  -0.0391   1.0000   0.0692
  -8.250  -0.5724   0.06505   0.06158  -0.0397   1.0000   0.0707
  -8.000  -0.5868   0.06057   0.05698  -0.0397   1.0000   0.0727
  -7.750  -0.6582   0.04050   0.03542  -0.0354   1.0000   0.0406
  -7.500  -0.6563   0.03633   0.03096  -0.0328   1.0000   0.0398
  -7.250  -0.6508   0.03286   0.02711  -0.0301   1.0000   0.0395
  -7.000  -0.6399   0.03074   0.02455  -0.0276   1.0000   0.0406
  -6.750  -0.6266   0.02917   0.02260  -0.0252   1.0000   0.0413
  -6.500  -0.6138   0.02583   0.01886  -0.0231   1.0000   0.0417
  -6.250  -0.5973   0.02333   0.01610  -0.0215   1.0000   0.0426
  -6.000  -0.5788   0.02192   0.01459  -0.0200   1.0000   0.0441
  -5.750  -0.5597   0.02107   0.01365  -0.0186   1.0000   0.0465
  -5.500  -0.5398   0.02008   0.01251  -0.0172   1.0000   0.0487
  -5.250  -0.5192   0.01909   0.01135  -0.0157   1.0000   0.0504
  -5.000  -0.4985   0.01815   0.01026  -0.0144   1.0000   0.0521
  -4.750  -0.4787   0.01703   0.00920  -0.0132   1.0000   0.0559
  -4.500  -0.4584   0.01651   0.00865  -0.0119   1.0000   0.0607
  -4.250  -0.4385   0.01574   0.00784  -0.0106   1.0000   0.0655
  -4.000  -0.4188   0.01516   0.00731  -0.0094   1.0000   0.0734
  -3.750  -0.3804   0.01442   0.00669  -0.0119   0.9954   0.0957
  -3.500  -0.3424   0.01376   0.00623  -0.0144   0.9900   0.1370
  -3.250  -0.3033   0.01318   0.00598  -0.0173   0.9847   0.2019
  -3.000  -0.2679   0.01249   0.00577  -0.0194   0.9782   0.3043
  -2.750  -0.2318   0.01168   0.00566  -0.0217   0.9723   0.4592
  -2.500  -0.2022   0.01093   0.00563  -0.0220   0.9646   0.6190
  -2.250  -0.1694   0.01064   0.00587  -0.0220   0.9585   0.7669
  -2.000  -0.1391   0.01063   0.00593  -0.0216   0.9500   0.8318
  -1.750  -0.1020   0.01066   0.00596  -0.0225   0.9443   0.8749
  -1.500  -0.0693   0.01070   0.00598  -0.0224   0.9363   0.9059
  -1.250  -0.0244   0.01076   0.00598  -0.0248   0.9318   0.9310
  -1.000   0.0330   0.01083   0.00596  -0.0299   0.9299   0.9472
  -0.750   0.0955   0.01084   0.00589  -0.0363   0.9283   0.9587
  -0.500   0.1553   0.01080   0.00579  -0.0423   0.9226   0.9682
  -0.250   0.2165   0.01061   0.00555  -0.0487   0.9172   0.9755
   0.000   0.2714   0.01039   0.00529  -0.0540   0.9085   0.9838
   0.250   0.3296   0.01006   0.00493  -0.0599   0.8985   0.9900
   0.500   0.3787   0.00977   0.00461  -0.0641   0.8821   0.9967
   0.750   0.4145   0.00957   0.00434  -0.0656   0.8592   1.0000
   1.000   0.4379   0.00948   0.00417  -0.0645   0.8356   1.0000
   1.250   0.4595   0.00944   0.00405  -0.0630   0.8111   1.0000
   1.500   0.4802   0.00944   0.00397  -0.0615   0.7865   1.0000
   1.750   0.5010   0.00945   0.00388  -0.0599   0.7622   1.0000
   2.000   0.5210   0.00949   0.00383  -0.0582   0.7360   1.0000
   2.250   0.5409   0.00955   0.00381  -0.0565   0.7102   1.0000
   2.500   0.5610   0.00964   0.00381  -0.0549   0.6863   1.0000
   2.750   0.5808   0.00974   0.00384  -0.0532   0.6618   1.0000
   3.000   0.6000   0.00987   0.00389  -0.0514   0.6360   1.0000
   3.250   0.6186   0.01003   0.00396  -0.0495   0.6091   1.0000
   3.500   0.6368   0.01021   0.00404  -0.0475   0.5812   1.0000
   3.750   0.6545   0.01042   0.00414  -0.0455   0.5526   1.0000
   4.000   0.6723   0.01064   0.00427  -0.0435   0.5250   1.0000
   4.250   0.6900   0.01088   0.00444  -0.0415   0.4962   1.0000
   4.500   0.7077   0.01114   0.00461  -0.0395   0.4663   1.0000
   4.750   0.7254   0.01144   0.00480  -0.0375   0.4356   1.0000
   5.000   0.7434   0.01177   0.00503  -0.0356   0.4019   1.0000
   5.250   0.7612   0.01216   0.00530  -0.0337   0.3645   1.0000
   5.500   0.7790   0.01262   0.00560  -0.0319   0.3235   1.0000
   5.750   0.7966   0.01318   0.00597  -0.0301   0.2794   1.0000
   6.000   0.8144   0.01382   0.00640  -0.0284   0.2389   1.0000
   6.250   0.8329   0.01447   0.00690  -0.0269   0.2066   1.0000
   6.500   0.8517   0.01516   0.00745  -0.0255   0.1811   1.0000
   6.750   0.8704   0.01589   0.00806  -0.0241   0.1605   1.0000
   7.000   0.8886   0.01672   0.00878  -0.0226   0.1437   1.0000
   7.250   0.9077   0.01749   0.00950  -0.0213   0.1291   1.0000
   7.500   0.9282   0.01811   0.01016  -0.0202   0.1164   1.0000
   7.750   0.9486   0.01874   0.01083  -0.0190   0.1053   1.0000
   8.000   0.9679   0.01955   0.01164  -0.0177   0.0959   1.0000
   8.250   0.9858   0.02051   0.01255  -0.0164   0.0875   1.0000
   8.500   1.0057   0.02118   0.01333  -0.0152   0.0796   1.0000
   8.750   1.0234   0.02234   0.01450  -0.0138   0.0731   1.0000
   9.000   1.0418   0.02310   0.01532  -0.0125   0.0667   1.0000
   9.250   1.0591   0.02442   0.01668  -0.0111   0.0613   1.0000
   9.500   1.0765   0.02516   0.01752  -0.0097   0.0559   1.0000
   9.750   1.0925   0.02676   0.01913  -0.0084   0.0513   1.0000
  10.000   1.1084   0.02757   0.02013  -0.0068   0.0471   1.0000
  10.250   1.1229   0.02872   0.02128  -0.0053   0.0435   1.0000
  10.500   1.1367   0.03059   0.02333  -0.0037   0.0402   1.0000
  10.750   1.1485   0.03172   0.02464  -0.0016   0.0374   1.0000
  11.000   1.1580   0.03275   0.02568   0.0005   0.0350   1.0000
  11.250   1.1678   0.03565   0.02873   0.0020   0.0328   1.0000
  11.500   1.1725   0.03738   0.03077   0.0047   0.0316   1.0000
  11.750   1.1753   0.03936   0.03300   0.0072   0.0303   1.0000
  12.000   1.1770   0.04130   0.03514   0.0094   0.0292   1.0000
  12.250   1.1785   0.04289   0.03683   0.0114   0.0280   1.0000
  12.500   1.1808   0.04484   0.03882   0.0128   0.0270   1.0000
  12.750   1.1741   0.04875   0.04291   0.0142   0.0261   1.0000
  13.000   1.1616   0.05239   0.04682   0.0155   0.0259   1.0000
  13.250   1.1489   0.05571   0.05040   0.0161   0.0256   1.0000
  13.500   1.1332   0.05982   0.05477   0.0158   0.0254   1.0000
  13.750   1.1150   0.06471   0.05991   0.0145   0.0253   1.0000
  14.000   1.0956   0.07033   0.06576   0.0122   0.0253   1.0000
  14.250   1.0739   0.07676   0.07241   0.0088   0.0253   1.0000
  14.500   1.0512   0.08408   0.07991   0.0047   0.0255   1.0000
  14.750   1.0276   0.09217   0.08816  -0.0003   0.0257   1.0000
  15.000   1.0001   0.10178   0.09793  -0.0065   0.0259   1.0000
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