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RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RG 14 9% AIRFOIL (rg149-il)
Reynolds number: 50,000
Max Cl/Cd: 33.12 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg149-il-50000.txt
Download as CSV file: xf-rg149-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9% 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4828   0.10901   0.10186  -0.0052   1.0000   0.2594
  -9.000  -0.5025   0.10811   0.10109  -0.0066   1.0000   0.2699
  -8.750  -0.4842   0.10339   0.09636  -0.0054   1.0000   0.2832
  -8.500  -0.4763   0.09977   0.09277  -0.0047   1.0000   0.2968
  -8.250  -0.4770   0.09695   0.09000  -0.0042   1.0000   0.3123
  -8.000  -0.4813   0.09449   0.08763  -0.0035   1.0000   0.3279
  -7.750  -0.4651   0.09024   0.08338  -0.0020   1.0000   0.3461
  -7.500  -0.4575   0.08693   0.08011  -0.0008   1.0000   0.3624
  -7.250  -0.4524   0.08380   0.07703   0.0004   1.0000   0.3790
  -7.000  -0.4498   0.08089   0.07419   0.0018   1.0000   0.3961
  -6.750  -0.4628   0.07899   0.07243   0.0042   1.0000   0.4175
  -6.500  -0.4462   0.07513   0.06856   0.0056   1.0000   0.4353
  -6.250  -0.5371   0.05428   0.04692  -0.0310   1.0000   0.1521
  -6.000  -0.5290   0.04900   0.04122  -0.0310   1.0000   0.1421
  -5.750  -0.5157   0.04484   0.03664  -0.0302   1.0000   0.1363
  -5.500  -0.5009   0.04089   0.03226  -0.0292   1.0000   0.1322
  -5.250  -0.4840   0.03725   0.02803  -0.0281   1.0000   0.1297
  -5.000  -0.4650   0.03458   0.02495  -0.0268   1.0000   0.1329
  -4.750  -0.4444   0.03217   0.02198  -0.0255   1.0000   0.1382
  -4.500  -0.4224   0.02972   0.01924  -0.0243   1.0000   0.1428
  -4.250  -0.3991   0.02772   0.01699  -0.0231   1.0000   0.1505
  -4.000  -0.3763   0.02603   0.01514  -0.0218   1.0000   0.1663
  -3.750  -0.3525   0.02426   0.01340  -0.0205   1.0000   0.1867
  -3.500  -0.3294   0.02266   0.01193  -0.0191   1.0000   0.2282
  -3.250  -0.3075   0.02083   0.01063  -0.0177   1.0000   0.3114
  -3.000  -0.2966   0.01814   0.00965  -0.0138   1.0000   0.5234
  -2.750  -0.1107   0.01822   0.00961  -0.0330   1.0000   1.0000
  -2.500  -0.1074   0.01789   0.00910  -0.0300   1.0000   1.0000
  -2.250  -0.1035   0.01766   0.00872  -0.0269   1.0000   1.0000
  -2.000  -0.0993   0.01750   0.00838  -0.0236   1.0000   1.0000
  -1.750  -0.0945   0.01740   0.00814  -0.0204   1.0000   1.0000
  -1.500  -0.0886   0.01736   0.00794  -0.0173   1.0000   1.0000
  -1.250  -0.0814   0.01737   0.00779  -0.0145   1.0000   1.0000
  -1.000  -0.0722   0.01743   0.00771  -0.0120   1.0000   1.0000
  -0.750  -0.0610   0.01755   0.00768  -0.0099   1.0000   1.0000
  -0.500  -0.0482   0.01773   0.00770  -0.0082   1.0000   1.0000
  -0.250  -0.0342   0.01795   0.00780  -0.0067   1.0000   1.0000
   0.000  -0.0194   0.01823   0.00797  -0.0054   1.0000   1.0000
   0.250  -0.0042   0.01857   0.00820  -0.0044   1.0000   1.0000
   0.500   0.0112   0.01895   0.00849  -0.0034   1.0000   1.0000
   0.750   0.0268   0.01940   0.00887  -0.0026   1.0000   1.0000
   1.000   0.0423   0.01991   0.00932  -0.0020   1.0000   1.0000
   1.250   0.0577   0.02048   0.00984  -0.0015   1.0000   1.0000
   1.500   0.0731   0.02112   0.01045  -0.0011   1.0000   1.0000
   1.750   0.0956   0.02195   0.01126  -0.0022   0.9967   1.0000
   2.000   0.1572   0.02334   0.01269  -0.0104   0.9748   1.0000
   2.250   0.2148   0.02446   0.01389  -0.0175   0.9523   1.0000
   2.500   0.2730   0.02538   0.01492  -0.0241   0.9298   1.0000
   2.750   0.3224   0.02604   0.01571  -0.0289   0.9055   1.0000
   3.000   0.3771   0.02654   0.01639  -0.0339   0.8815   1.0000
   3.250   0.4361   0.02672   0.01680  -0.0391   0.8572   1.0000
   3.500   0.4928   0.02655   0.01691  -0.0431   0.8300   1.0000
   3.750   0.5575   0.02551   0.01617  -0.0465   0.7992   1.0000
   4.000   0.6054   0.02462   0.01553  -0.0469   0.7672   1.0000
   4.250   0.6403   0.02418   0.01526  -0.0457   0.7347   1.0000
   4.500   0.6745   0.02365   0.01486  -0.0440   0.6997   1.0000
   4.750   0.7027   0.02327   0.01455  -0.0414   0.6596   1.0000
   5.000   0.7282   0.02298   0.01427  -0.0383   0.6135   1.0000
   5.250   0.7499   0.02293   0.01409  -0.0348   0.5601   1.0000
   5.500   0.7687   0.02321   0.01413  -0.0313   0.4996   1.0000
   5.750   0.7864   0.02387   0.01443  -0.0280   0.4366   1.0000
   6.000   0.8036   0.02489   0.01515  -0.0252   0.3787   1.0000
   6.250   0.8215   0.02615   0.01614  -0.0230   0.3294   1.0000
   6.500   0.8419   0.02764   0.01735  -0.0212   0.2893   1.0000
   6.750   0.8611   0.02923   0.01891  -0.0195   0.2554   1.0000
   7.000   0.8828   0.03109   0.02071  -0.0182   0.2290   1.0000
   7.250   0.9043   0.03297   0.02255  -0.0171   0.2058   1.0000
   7.500   0.9244   0.03529   0.02505  -0.0157   0.1881   1.0000
   7.750   0.9426   0.03769   0.02769  -0.0142   0.1724   1.0000
   8.000   0.9619   0.04058   0.03074  -0.0130   0.1608   1.0000
   8.250   0.9799   0.04336   0.03359  -0.0118   0.1483   1.0000
   8.500   0.9848   0.04707   0.03811  -0.0092   0.1435   1.0000
   8.750   1.0042   0.05044   0.04137  -0.0084   0.1344   1.0000
   9.000   0.9984   0.05437   0.04608  -0.0055   0.1312   1.0000
   9.250   0.9923   0.05884   0.05110  -0.0033   0.1293   1.0000
   9.500   0.9812   0.06378   0.05644  -0.0015   0.1293   1.0000
   9.750   0.9651   0.06887   0.06179  -0.0001   0.1301   1.0000
  10.000   0.9464   0.07404   0.06714   0.0007   0.1315   1.0000
  10.250   0.9272   0.07911   0.07230   0.0012   0.1328   1.0000
  10.500   0.9125   0.08464   0.07788   0.0008   0.1339   1.0000
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