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RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAE 100 AIRFOIL (rae100-il)
Reynolds number: 500,000
Max Cl/Cd: 60.44 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae100-il-500000.txt
Download as CSV file: xf-rae100-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 100 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
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.9325   0.10362   0.10093   0.0020   1.0000   0.0169
 -15.000  -0.9808   0.08873   0.08583  -0.0076   1.0000   0.0165
 -14.750  -1.0242   0.07608   0.07295  -0.0161   1.0000   0.0160
 -14.500  -1.0511   0.06730   0.06397  -0.0221   1.0000   0.0159
 -14.250  -1.0710   0.06031   0.05680  -0.0269   1.0000   0.0160
 -14.000  -1.0865   0.05451   0.05083  -0.0305   1.0000   0.0160
 -13.750  -1.1010   0.04937   0.04549  -0.0333   1.0000   0.0160
 -13.500  -1.1099   0.04548   0.04144  -0.0350   1.0000   0.0164
 -13.250  -1.1179   0.04208   0.03786  -0.0358   1.0000   0.0164
 -13.000  -1.1251   0.03912   0.03473  -0.0356   1.0000   0.0166
 -12.750  -1.1302   0.03672   0.03215  -0.0345   1.0000   0.0169
 -12.500  -1.1334   0.03468   0.02993  -0.0327   1.0000   0.0170
 -12.250  -1.1337   0.03310   0.02818  -0.0302   1.0000   0.0173
 -12.000  -1.1319   0.03170   0.02660  -0.0275   1.0000   0.0175
 -11.750  -1.1293   0.02953   0.02423  -0.0251   1.0000   0.0178
 -11.500  -1.1227   0.02747   0.02205  -0.0231   1.0000   0.0183
 -11.250  -1.1098   0.02625   0.02076  -0.0216   1.0000   0.0188
 -11.000  -1.0941   0.02531   0.01975  -0.0203   1.0000   0.0193
 -10.750  -1.0778   0.02429   0.01864  -0.0190   1.0000   0.0199
 -10.500  -1.0602   0.02339   0.01763  -0.0178   1.0000   0.0207
 -10.250  -1.0410   0.02264   0.01677  -0.0167   1.0000   0.0215
 -10.000  -1.0215   0.02185   0.01586  -0.0156   1.0000   0.0221
  -9.750  -1.0075   0.02020   0.01412  -0.0139   1.0000   0.0231
  -9.500  -0.9876   0.01943   0.01333  -0.0129   1.0000   0.0241
  -9.250  -0.9668   0.01875   0.01260  -0.0119   1.0000   0.0252
  -9.000  -0.9455   0.01810   0.01187  -0.0109   1.0000   0.0264
  -8.750  -0.9227   0.01763   0.01131  -0.0101   1.0000   0.0273
  -8.500  -0.9056   0.01642   0.01007  -0.0086   1.0000   0.0293
  -8.250  -0.8833   0.01590   0.00953  -0.0077   1.0000   0.0311
  -8.000  -0.8607   0.01540   0.00897  -0.0068   1.0000   0.0329
  -7.750  -0.8399   0.01467   0.00817  -0.0056   1.0000   0.0349
  -7.500  -0.8182   0.01408   0.00758  -0.0046   1.0000   0.0377
  -7.250  -0.7948   0.01370   0.00717  -0.0037   1.0000   0.0406
  -7.000  -0.7735   0.01307   0.00652  -0.0025   1.0000   0.0443
  -6.750  -0.7506   0.01265   0.00610  -0.0016   1.0000   0.0485
  -6.500  -0.7282   0.01217   0.00560  -0.0005   1.0000   0.0537
  -6.250  -0.7052   0.01179   0.00523   0.0004   1.0000   0.0600
  -6.000  -0.6828   0.01133   0.00482   0.0014   1.0000   0.0686
  -5.750  -0.6601   0.01093   0.00446   0.0024   1.0000   0.0790
  -5.500  -0.6374   0.01054   0.00413   0.0034   1.0000   0.0927
  -5.250  -0.6148   0.01018   0.00384   0.0044   1.0000   0.1097
  -5.000  -0.5924   0.00981   0.00357   0.0055   1.0000   0.1305
  -4.750  -0.5700   0.00947   0.00333   0.0065   1.0000   0.1543
  -4.500  -0.5478   0.00913   0.00311   0.0076   1.0000   0.1810
  -4.250  -0.5258   0.00882   0.00293   0.0087   1.0000   0.2096
  -4.000  -0.5039   0.00854   0.00277   0.0098   1.0000   0.2396
  -3.750  -0.4822   0.00828   0.00264   0.0109   1.0000   0.2705
  -3.500  -0.4535   0.00803   0.00252   0.0106   0.9984   0.3053
  -3.250  -0.4136   0.00776   0.00242   0.0079   0.9937   0.3463
  -3.000  -0.3757   0.00750   0.00230   0.0057   0.9877   0.3850
  -2.750  -0.3357   0.00726   0.00221   0.0031   0.9827   0.4243
  -2.500  -0.2992   0.00702   0.00211   0.0013   0.9745   0.4601
  -2.250  -0.2608   0.00680   0.00202  -0.0009   0.9671   0.4954
  -2.000  -0.2237   0.00660   0.00193  -0.0027   0.9564   0.5291
  -1.750  -0.1887   0.00641   0.00185  -0.0040   0.9416   0.5614
  -1.500  -0.1564   0.00626   0.00177  -0.0046   0.9212   0.5910
  -1.250  -0.1270   0.00615   0.00170  -0.0045   0.8964   0.6198
  -1.000  -0.1005   0.00608   0.00165  -0.0038   0.8681   0.6471
  -0.750  -0.0750   0.00604   0.00161  -0.0029   0.8391   0.6744
  -0.500  -0.0500   0.00602   0.00158  -0.0019   0.8103   0.7009
  -0.250  -0.0250   0.00601   0.00156  -0.0010   0.7823   0.7275
   0.000   0.0000   0.00602   0.00156   0.0000   0.7547   0.7547
   0.250   0.0250   0.00601   0.00156   0.0010   0.7275   0.7824
   0.500   0.0499   0.00602   0.00158   0.0019   0.7009   0.8103
   0.750   0.0749   0.00604   0.00161   0.0029   0.6742   0.8391
   1.000   0.1005   0.00608   0.00165   0.0038   0.6471   0.8681
   1.250   0.1270   0.00615   0.00170   0.0045   0.6197   0.8964
   1.500   0.1564   0.00626   0.00177   0.0046   0.5910   0.9212
   1.750   0.1887   0.00641   0.00185   0.0039   0.5613   0.9416
   2.000   0.2236   0.00660   0.00193   0.0027   0.5292   0.9563
   2.250   0.2608   0.00680   0.00202   0.0009   0.4955   0.9669
   2.500   0.2992   0.00703   0.00211  -0.0013   0.4600   0.9744
   2.750   0.3357   0.00726   0.00221  -0.0031   0.4240   0.9826
   3.000   0.3757   0.00750   0.00231  -0.0057   0.3849   0.9877
   3.250   0.4137   0.00776   0.00242  -0.0079   0.3466   0.9936
   3.500   0.4534   0.00803   0.00253  -0.0106   0.3054   0.9984
   3.750   0.4824   0.00828   0.00264  -0.0110   0.2703   1.0000
   4.000   0.5041   0.00854   0.00277  -0.0098   0.2395   1.0000
   4.250   0.5261   0.00882   0.00293  -0.0087   0.2096   1.0000
   4.500   0.5481   0.00913   0.00312  -0.0076   0.1811   1.0000
   4.750   0.5702   0.00947   0.00333  -0.0066   0.1542   1.0000
   5.000   0.5926   0.00981   0.00357  -0.0055   0.1303   1.0000
   5.250   0.6150   0.01018   0.00384  -0.0045   0.1096   1.0000
   5.500   0.6376   0.01055   0.00413  -0.0035   0.0927   1.0000
   5.750   0.6603   0.01093   0.00446  -0.0025   0.0790   1.0000
   6.000   0.6830   0.01133   0.00482  -0.0015   0.0685   1.0000
   6.250   0.7053   0.01180   0.00524  -0.0004   0.0600   1.0000
   6.500   0.7284   0.01217   0.00560   0.0005   0.0538   1.0000
   6.750   0.7508   0.01265   0.00610   0.0016   0.0484   1.0000
   7.000   0.7736   0.01307   0.00652   0.0025   0.0443   1.0000
   7.250   0.7948   0.01370   0.00717   0.0037   0.0406   1.0000
   7.500   0.8181   0.01409   0.00759   0.0046   0.0377   1.0000
   7.750   0.8398   0.01468   0.00818   0.0056   0.0349   1.0000
   8.000   0.8605   0.01541   0.00898   0.0068   0.0329   1.0000
   8.250   0.8832   0.01590   0.00952   0.0077   0.0311   1.0000
   8.500   0.9055   0.01641   0.01006   0.0086   0.0293   1.0000
   8.750   0.9229   0.01758   0.01126   0.0100   0.0274   1.0000
   9.000   0.9453   0.01809   0.01186   0.0109   0.0264   1.0000
   9.250   0.9666   0.01875   0.01260   0.0119   0.0253   1.0000
   9.500   0.9875   0.01942   0.01332   0.0129   0.0241   1.0000
   9.750   1.0072   0.02020   0.01414   0.0140   0.0232   1.0000
  10.000   1.0217   0.02176   0.01577   0.0156   0.0222   1.0000
  10.250   1.0408   0.02260   0.01673   0.0167   0.0214   1.0000
  10.500   1.0594   0.02345   0.01770   0.0179   0.0208   1.0000
  10.750   1.0773   0.02429   0.01864   0.0191   0.0199   1.0000
  11.000   1.0939   0.02522   0.01966   0.0204   0.0193   1.0000
  11.250   1.1094   0.02620   0.02072   0.0217   0.0188   1.0000
  11.500   1.1222   0.02747   0.02206   0.0233   0.0184   1.0000
  11.750   1.1280   0.02960   0.02431   0.0253   0.0178   1.0000
  12.000   1.1320   0.03147   0.02638   0.0276   0.0174   1.0000
  12.250   1.1345   0.03280   0.02787   0.0303   0.0172   1.0000
  12.500   1.1334   0.03458   0.02982   0.0327   0.0170   1.0000
  12.750   1.1306   0.03657   0.03199   0.0346   0.0168   1.0000
  13.000   1.1254   0.03901   0.03461   0.0357   0.0166   1.0000
  13.250   1.1184   0.04194   0.03772   0.0358   0.0164   1.0000
  13.500   1.1093   0.04549   0.04145   0.0350   0.0163   1.0000
  13.750   1.1003   0.04943   0.04555   0.0333   0.0161   1.0000
  14.000   1.0902   0.05392   0.05020   0.0308   0.0159   1.0000
  14.250   1.0694   0.06054   0.05704   0.0267   0.0160   1.0000
  14.500   1.0484   0.06778   0.06447   0.0218   0.0160   1.0000
  14.750   1.0188   0.07712   0.07402   0.0154   0.0161   1.0000
  15.000   0.9779   0.08940   0.08652   0.0071   0.0165   1.0000
  15.250   0.9297   0.10440   0.10172  -0.0026   0.0169   1.0000
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