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RG-12 (rg12-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG-12 (rg12-il)
Reynolds number: 200,000
Max Cl/Cd: 64.18 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12-il-200000.txt
Download as CSV file: xf-rg12-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG-12                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4963   0.10392   0.10026  -0.0201   1.0000   0.0461
  -9.750  -0.4969   0.09993   0.09631  -0.0219   1.0000   0.0476
  -9.500  -0.5002   0.09555   0.09198  -0.0246   1.0000   0.0493
  -9.250  -0.4442   0.07805   0.07479  -0.0362   1.0000   0.0527
  -9.000  -0.4341   0.07542   0.07217  -0.0335   1.0000   0.0539
  -8.750  -0.4331   0.07192   0.06869  -0.0332   1.0000   0.0550
  -8.500  -0.4388   0.06762   0.06443  -0.0343   1.0000   0.0558
  -8.250  -0.4508   0.06268   0.05953  -0.0366   1.0000   0.0564
  -7.750  -0.5756   0.06196   0.05841  -0.0403   1.0000   0.0538
  -7.500  -0.5711   0.05925   0.05571  -0.0390   1.0000   0.0549
  -7.250  -0.5690   0.05628   0.05267  -0.0379   1.0000   0.0562
  -7.000  -0.5670   0.05308   0.04937  -0.0367   1.0000   0.0581
  -6.750  -0.5651   0.04962   0.04565  -0.0355   1.0000   0.0616
  -6.500  -0.5682   0.04531   0.04090  -0.0338   1.0000   0.0663
  -6.250  -0.5642   0.03571   0.03033  -0.0304   1.0000   0.0409
  -6.000  -0.5490   0.03014   0.02403  -0.0272   1.0000   0.0287
  -5.750  -0.5327   0.02714   0.02075  -0.0256   1.0000   0.0277
  -5.500  -0.5153   0.02426   0.01748  -0.0240   1.0000   0.0274
  -5.250  -0.4954   0.02227   0.01515  -0.0224   1.0000   0.0278
  -5.000  -0.4743   0.02075   0.01336  -0.0211   1.0000   0.0282
  -4.750  -0.4540   0.01844   0.01091  -0.0200   1.0000   0.0313
  -4.500  -0.4327   0.01747   0.00985  -0.0188   1.0000   0.0339
  -4.250  -0.4108   0.01642   0.00872  -0.0176   1.0000   0.0360
  -4.000  -0.3890   0.01560   0.00779  -0.0164   1.0000   0.0393
  -3.750  -0.3678   0.01431   0.00655  -0.0153   1.0000   0.0529
  -3.500  -0.3465   0.01345   0.00585  -0.0145   1.0000   0.0876
  -3.250  -0.3253   0.01279   0.00551  -0.0138   1.0000   0.1455
  -3.000  -0.3046   0.01193   0.00522  -0.0133   1.0000   0.2556
  -2.750  -0.2740   0.01090   0.00505  -0.0149   0.9967   0.4571
  -2.500  -0.2427   0.01028   0.00541  -0.0154   0.9907   0.6933
  -2.250  -0.2064   0.01045   0.00570  -0.0165   0.9839   0.7806
  -2.000  -0.1735   0.01055   0.00582  -0.0169   0.9757   0.8252
  -1.750  -0.1370   0.01069   0.00590  -0.0180   0.9693   0.8595
  -1.500  -0.1070   0.01069   0.00587  -0.0177   0.9599   0.8844
  -1.250  -0.0749   0.01068   0.00583  -0.0177   0.9519   0.9065
  -1.000  -0.0381   0.01066   0.00575  -0.0188   0.9451   0.9265
  -0.750   0.0008   0.01064   0.00566  -0.0204   0.9379   0.9430
  -0.500   0.0496   0.01062   0.00558  -0.0241   0.9331   0.9560
  -0.250   0.1102   0.01058   0.00548  -0.0304   0.9311   0.9634
   0.000   0.1652   0.01048   0.00533  -0.0356   0.9260   0.9705
   0.250   0.2246   0.01030   0.00513  -0.0418   0.9201   0.9753
   0.500   0.2769   0.01008   0.00489  -0.0466   0.9115   0.9808
   0.750   0.3277   0.00981   0.00462  -0.0511   0.9001   0.9846
   1.000   0.3742   0.00958   0.00438  -0.0548   0.8835   0.9887
   1.250   0.4161   0.00939   0.00416  -0.0575   0.8635   0.9932
   1.500   0.4561   0.00922   0.00395  -0.0599   0.8401   0.9974
   1.750   0.4878   0.00914   0.00383  -0.0606   0.8146   1.0000
   2.000   0.5087   0.00913   0.00374  -0.0591   0.7878   1.0000
   2.250   0.5286   0.00916   0.00368  -0.0575   0.7607   1.0000
   2.500   0.5476   0.00921   0.00365  -0.0557   0.7330   1.0000
   2.750   0.5657   0.00929   0.00365  -0.0538   0.7046   1.0000
   3.000   0.5832   0.00941   0.00371  -0.0517   0.6760   1.0000
   3.250   0.5999   0.00955   0.00377  -0.0496   0.6472   1.0000
   3.500   0.6163   0.00972   0.00386  -0.0473   0.6180   1.0000
   3.750   0.6327   0.00992   0.00397  -0.0451   0.5880   1.0000
   4.000   0.6499   0.01016   0.00410  -0.0430   0.5569   1.0000
   4.250   0.6686   0.01043   0.00426  -0.0412   0.5245   1.0000
   4.500   0.6887   0.01073   0.00449  -0.0398   0.4898   1.0000
   4.750   0.7094   0.01107   0.00472  -0.0384   0.4549   1.0000
   5.000   0.7307   0.01144   0.00499  -0.0372   0.4175   1.0000
   5.250   0.7519   0.01185   0.00529  -0.0361   0.3788   1.0000
   5.500   0.7731   0.01231   0.00562  -0.0349   0.3382   1.0000
   5.750   0.7939   0.01284   0.00604  -0.0338   0.2942   1.0000
   6.000   0.8142   0.01346   0.00648  -0.0327   0.2484   1.0000
   6.250   0.8343   0.01416   0.00699  -0.0316   0.2013   1.0000
   6.500   0.8539   0.01497   0.00758  -0.0305   0.1562   1.0000
   6.750   0.8731   0.01588   0.00830  -0.0293   0.1175   1.0000
   7.000   0.8912   0.01694   0.00919  -0.0279   0.0872   1.0000
   7.250   0.9086   0.01814   0.01033  -0.0263   0.0653   1.0000
   7.500   0.9259   0.01935   0.01156  -0.0247   0.0516   1.0000
   7.750   0.9428   0.02070   0.01294  -0.0230   0.0429   1.0000
   8.000   0.9584   0.02229   0.01452  -0.0213   0.0362   1.0000
   8.250   0.9782   0.02332   0.01570  -0.0201   0.0311   1.0000
   8.500   0.9938   0.02549   0.01789  -0.0185   0.0275   1.0000
   8.750   1.0126   0.02794   0.02057  -0.0171   0.0255   1.0000
   9.000   1.0312   0.02927   0.02211  -0.0158   0.0229   1.0000
   9.250   1.0478   0.03079   0.02381  -0.0144   0.0209   1.0000
   9.500   1.0628   0.03306   0.02630  -0.0129   0.0199   1.0000
   9.750   1.0751   0.03576   0.02929  -0.0113   0.0193   1.0000
  10.000   1.0832   0.03891   0.03276  -0.0093   0.0190   1.0000
  10.250   1.0861   0.04232   0.03653  -0.0068   0.0188   1.0000
  10.500   1.0851   0.04548   0.04004  -0.0041   0.0189   1.0000
  10.750   1.0767   0.04853   0.04343  -0.0007   0.0192   1.0000
  11.000   1.0613   0.05201   0.04724   0.0028   0.0195   1.0000
  11.250   1.0392   0.05633   0.05192   0.0053   0.0201   1.0000
  11.500   1.0101   0.06144   0.05737   0.0059   0.0206   1.0000
  11.750   0.9822   0.06737   0.06356   0.0043   0.0210   1.0000
  12.000   0.9565   0.07401   0.07042   0.0007   0.0213   1.0000
  12.250   0.9292   0.08227   0.07881  -0.0051   0.0217   1.0000
  12.500   0.8994   0.09294   0.08963  -0.0132   0.0222   1.0000
  12.750   0.8641   0.10768   0.10446  -0.0234   0.0232   1.0000
  13.000   0.8393   0.12089   0.11764  -0.0305   0.0247   1.0000
  13.250   0.8256   0.13031   0.12702  -0.0351   0.0254   1.0000
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