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RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RG 14 9.5% AIRFOIL (rg1495-il)
Reynolds number: 500,000
Max Cl/Cd: 82.08 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg1495-il-500000.txt
Download as CSV file: xf-rg1495-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9.5% AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5318   0.09195   0.08960  -0.0249   1.0000   0.0240
 -10.000  -0.6174   0.06016   0.05786  -0.0457   1.0000   0.0164
  -9.750  -0.6459   0.05361   0.05119  -0.0504   1.0000   0.0160
  -9.500  -0.6757   0.04956   0.04701  -0.0483   1.0000   0.0159
  -9.250  -0.7033   0.04411   0.04133  -0.0459   1.0000   0.0155
  -9.000  -0.7223   0.03893   0.03579  -0.0427   1.0000   0.0156
  -8.750  -0.7343   0.03414   0.03056  -0.0391   1.0000   0.0156
  -8.500  -0.7335   0.03097   0.02700  -0.0361   1.0000   0.0162
  -8.250  -0.7274   0.02845   0.02411  -0.0333   1.0000   0.0165
  -8.000  -0.7168   0.02668   0.02202  -0.0308   1.0000   0.0168
  -7.750  -0.7117   0.02305   0.01793  -0.0279   1.0000   0.0173
  -7.500  -0.6987   0.02087   0.01552  -0.0258   1.0000   0.0177
  -7.250  -0.6817   0.01988   0.01446  -0.0242   1.0000   0.0185
  -7.000  -0.6637   0.01907   0.01356  -0.0227   1.0000   0.0193
  -6.750  -0.6452   0.01823   0.01261  -0.0211   1.0000   0.0201
  -6.500  -0.6218   0.01769   0.01195  -0.0205   0.9995   0.0214
  -6.250  -0.5864   0.01708   0.01117  -0.0222   0.9972   0.0223
  -6.000  -0.5558   0.01493   0.00885  -0.0233   0.9951   0.0237
  -5.750  -0.5218   0.01423   0.00812  -0.0248   0.9927   0.0253
  -5.500  -0.4877   0.01369   0.00753  -0.0263   0.9895   0.0272
  -5.250  -0.4525   0.01313   0.00690  -0.0279   0.9867   0.0286
  -5.000  -0.4172   0.01234   0.00603  -0.0296   0.9844   0.0302
  -4.750  -0.3843   0.01167   0.00535  -0.0309   0.9810   0.0331
  -4.500  -0.3508   0.01126   0.00491  -0.0321   0.9767   0.0361
  -4.250  -0.3149   0.01075   0.00436  -0.0338   0.9736   0.0402
  -4.000  -0.2772   0.01026   0.00390  -0.0359   0.9713   0.0511
  -3.750  -0.2465   0.00971   0.00352  -0.0366   0.9658   0.0824
  -3.500  -0.2117   0.00927   0.00324  -0.0382   0.9617   0.1204
  -3.250  -0.1744   0.00882   0.00298  -0.0404   0.9589   0.1674
  -3.000  -0.1398   0.00837   0.00275  -0.0420   0.9550   0.2269
  -2.750  -0.1101   0.00787   0.00254  -0.0425   0.9479   0.3030
  -2.500  -0.0767   0.00726   0.00232  -0.0439   0.9432   0.4097
  -2.250  -0.0508   0.00665   0.00215  -0.0436   0.9334   0.5309
  -2.000  -0.0234   0.00608   0.00202  -0.0434   0.9246   0.6538
  -1.750   0.0039   0.00577   0.00200  -0.0429   0.9144   0.7449
  -1.500   0.0304   0.00568   0.00200  -0.0421   0.9019   0.7956
  -1.250   0.0572   0.00565   0.00198  -0.0414   0.8888   0.8261
  -1.000   0.0833   0.00565   0.00197  -0.0405   0.8748   0.8496
  -0.750   0.1092   0.00567   0.00195  -0.0397   0.8599   0.8683
  -0.500   0.1346   0.00570   0.00194  -0.0387   0.8444   0.8832
  -0.250   0.1597   0.00574   0.00193  -0.0377   0.8281   0.8960
   0.000   0.1842   0.00579   0.00192  -0.0365   0.8099   0.9081
   0.250   0.2081   0.00585   0.00192  -0.0352   0.7886   0.9199
   0.500   0.2324   0.00592   0.00191  -0.0340   0.7684   0.9308
   0.750   0.2571   0.00600   0.00192  -0.0330   0.7490   0.9410
   1.000   0.2843   0.00609   0.00194  -0.0325   0.7275   0.9496
   1.250   0.3121   0.00620   0.00197  -0.0322   0.7068   0.9588
   1.500   0.3448   0.00632   0.00201  -0.0330   0.6837   0.9654
   1.750   0.3762   0.00646   0.00204  -0.0336   0.6581   0.9718
   2.000   0.4145   0.00663   0.00210  -0.0358   0.6322   0.9756
   2.250   0.4516   0.00678   0.00217  -0.0378   0.6067   0.9801
   2.500   0.4869   0.00696   0.00223  -0.0394   0.5768   0.9845
   2.750   0.5241   0.00715   0.00229  -0.0415   0.5421   0.9878
   3.000   0.5589   0.00734   0.00236  -0.0431   0.5091   0.9918
   3.250   0.5931   0.00755   0.00244  -0.0446   0.4745   0.9953
   3.500   0.6283   0.00777   0.00254  -0.0464   0.4409   0.9987
   3.750   0.6542   0.00797   0.00264  -0.0463   0.4112   1.0000
   4.000   0.6718   0.00819   0.00275  -0.0444   0.3810   1.0000
   4.250   0.6889   0.00844   0.00289  -0.0424   0.3493   1.0000
   4.500   0.7059   0.00871   0.00305  -0.0404   0.3178   1.0000
   4.750   0.7229   0.00906   0.00324  -0.0384   0.2809   1.0000
   5.000   0.7411   0.00945   0.00347  -0.0367   0.2422   1.0000
   5.250   0.7601   0.00989   0.00373  -0.0352   0.2038   1.0000
   5.500   0.7803   0.01034   0.00403  -0.0339   0.1725   1.0000
   5.750   0.8017   0.01077   0.00435  -0.0328   0.1521   1.0000
   6.000   0.8243   0.01114   0.00467  -0.0319   0.1363   1.0000
   6.250   0.8473   0.01150   0.00499  -0.0311   0.1206   1.0000
   6.500   0.8703   0.01188   0.00533  -0.0303   0.1041   1.0000
   6.750   0.8931   0.01230   0.00569  -0.0295   0.0906   1.0000
   7.000   0.9158   0.01274   0.00610  -0.0287   0.0801   1.0000
   7.250   0.9380   0.01323   0.00656  -0.0278   0.0705   1.0000
   7.500   0.9604   0.01371   0.00702  -0.0269   0.0618   1.0000
   7.750   0.9834   0.01411   0.00746  -0.0262   0.0551   1.0000
   8.000   1.0043   0.01473   0.00805  -0.0252   0.0481   1.0000
   8.250   1.0276   0.01509   0.00846  -0.0245   0.0434   1.0000
   8.500   1.0474   0.01580   0.00915  -0.0233   0.0381   1.0000
   8.750   1.0702   0.01620   0.00963  -0.0226   0.0347   1.0000
   9.000   1.0888   0.01699   0.01041  -0.0212   0.0303   1.0000
   9.250   1.1103   0.01748   0.01098  -0.0203   0.0274   1.0000
   9.500   1.1294   0.01818   0.01168  -0.0191   0.0239   1.0000
   9.750   1.1471   0.01898   0.01256  -0.0177   0.0213   1.0000
  10.000   1.1661   0.01963   0.01326  -0.0165   0.0191   1.0000
  10.250   1.1751   0.02109   0.01479  -0.0139   0.0171   1.0000
  10.500   1.1927   0.02178   0.01560  -0.0125   0.0162   1.0000
  10.750   1.2075   0.02264   0.01655  -0.0107   0.0151   1.0000
  11.000   1.2199   0.02347   0.01745  -0.0086   0.0143   1.0000
  11.250   1.2283   0.02450   0.01854  -0.0060   0.0136   1.0000
  11.500   1.2239   0.02653   0.02069  -0.0020   0.0128   1.0000
  11.750   1.2335   0.02753   0.02181   0.0000   0.0125   1.0000
  12.000   1.2415   0.02867   0.02308   0.0022   0.0120   1.0000
  12.250   1.2483   0.02990   0.02445   0.0041   0.0115   1.0000
  12.500   1.2525   0.03140   0.02607   0.0061   0.0111   1.0000
  12.750   1.2557   0.03305   0.02782   0.0078   0.0108   1.0000
  13.000   1.2563   0.03503   0.02993   0.0093   0.0106   1.0000
  13.250   1.2579   0.03696   0.03195   0.0103   0.0102   1.0000
  13.500   1.2550   0.03959   0.03471   0.0112   0.0101   1.0000
  13.750   1.2507   0.04251   0.03776   0.0117   0.0099   1.0000
  14.000   1.2432   0.04601   0.04140   0.0116   0.0097   1.0000
  14.250   1.2306   0.05044   0.04601   0.0109   0.0096   1.0000
  14.500   1.2167   0.05537   0.05113   0.0096   0.0095   1.0000
  14.750   1.2075   0.05994   0.05586   0.0079   0.0095   1.0000
  15.000   1.1877   0.06645   0.06258   0.0050   0.0094   1.0000
  15.250   1.1732   0.07247   0.06876   0.0019   0.0094   1.0000
  15.750   1.1447   0.08567   0.08230  -0.0057   0.0093   1.0000
  16.000   1.1255   0.09366   0.09045  -0.0104   0.0094   1.0000
  16.250   1.1067   0.10199   0.09893  -0.0155   0.0094   1.0000
  16.500   1.0879   0.11084   0.10792  -0.0209   0.0094   1.0000
  16.750   1.0752   0.11859   0.11580  -0.0257   0.0094   1.0000
  17.000   1.0572   0.12794   0.12528  -0.0314   0.0095   1.0000
  17.250   1.0389   0.13780   0.13526  -0.0374   0.0096   1.0000
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