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RAE 101 AIRFOIL (rae101-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAE 101 AIRFOIL (rae101-il)
Reynolds number: 200,000
Max Cl/Cd: 44.2 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae101-il-200000-n5.txt
Download as CSV file: xf-rae101-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 101 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.8145   0.07775   0.07397  -0.0142   1.0000   0.0136
 -12.000  -0.8518   0.06635   0.06238  -0.0228   1.0000   0.0133
 -11.750  -0.8767   0.05916   0.05497  -0.0277   1.0000   0.0132
 -11.500  -0.8993   0.05349   0.04907  -0.0304   1.0000   0.0132
 -11.250  -0.9185   0.04910   0.04444  -0.0310   1.0000   0.0132
 -11.000  -0.9326   0.04586   0.04098  -0.0298   1.0000   0.0134
 -10.750  -0.9448   0.04300   0.03787  -0.0273   1.0000   0.0135
 -10.500  -0.9492   0.04045   0.03504  -0.0249   1.0000   0.0139
 -10.250  -0.9484   0.03787   0.03214  -0.0228   1.0000   0.0144
 -10.000  -0.9436   0.03535   0.02924  -0.0209   1.0000   0.0150
  -9.750  -0.9342   0.03320   0.02668  -0.0191   1.0000   0.0155
  -9.500  -0.9232   0.03084   0.02407  -0.0175   1.0000   0.0159
  -9.250  -0.9088   0.02908   0.02216  -0.0162   1.0000   0.0164
  -9.000  -0.8921   0.02767   0.02061  -0.0151   1.0000   0.0170
  -8.750  -0.8744   0.02632   0.01912  -0.0139   1.0000   0.0176
  -8.500  -0.8559   0.02503   0.01767  -0.0127   1.0000   0.0185
  -8.250  -0.8368   0.02380   0.01627  -0.0116   1.0000   0.0194
  -8.000  -0.8165   0.02282   0.01510  -0.0105   1.0000   0.0207
  -7.750  -0.7982   0.02155   0.01376  -0.0093   1.0000   0.0221
  -7.500  -0.7786   0.02061   0.01278  -0.0081   1.0000   0.0234
  -7.250  -0.7586   0.01973   0.01182  -0.0070   1.0000   0.0248
  -7.000  -0.7384   0.01888   0.01088  -0.0058   1.0000   0.0265
  -6.750  -0.7179   0.01813   0.01002  -0.0046   1.0000   0.0287
  -6.500  -0.6984   0.01732   0.00921  -0.0034   1.0000   0.0315
  -6.250  -0.6776   0.01668   0.00850  -0.0022   1.0000   0.0345
  -6.000  -0.6567   0.01606   0.00780  -0.0010   1.0000   0.0377
  -5.750  -0.6364   0.01541   0.00717   0.0002   1.0000   0.0432
  -5.500  -0.6151   0.01487   0.00656   0.0014   1.0000   0.0493
  -5.250  -0.5940   0.01434   0.00603   0.0025   1.0000   0.0580
  -5.000  -0.5729   0.01381   0.00555   0.0037   1.0000   0.0714
  -4.750  -0.5521   0.01327   0.00511   0.0048   1.0000   0.0914
  -4.500  -0.5317   0.01271   0.00468   0.0060   1.0000   0.1242
  -4.250  -0.5122   0.01207   0.00429   0.0072   1.0000   0.1746
  -4.000  -0.4937   0.01136   0.00393   0.0085   1.0000   0.2490
  -3.750  -0.4754   0.01075   0.00372   0.0100   1.0000   0.3375
  -3.500  -0.4402   0.01035   0.00354   0.0081   0.9916   0.4054
  -3.250  -0.4043   0.01008   0.00341   0.0062   0.9831   0.4535
  -3.000  -0.3701   0.00985   0.00328   0.0048   0.9729   0.4913
  -2.750  -0.3358   0.00966   0.00316   0.0035   0.9619   0.5248
  -2.500  -0.3014   0.00948   0.00306   0.0021   0.9503   0.5562
  -2.250  -0.2670   0.00932   0.00297   0.0009   0.9374   0.5857
  -2.000  -0.2331   0.00917   0.00288  -0.0002   0.9228   0.6122
  -1.750  -0.1998   0.00904   0.00279  -0.0012   0.9060   0.6353
  -1.500  -0.1675   0.00893   0.00270  -0.0018   0.8876   0.6559
  -1.250  -0.1363   0.00885   0.00262  -0.0022   0.8680   0.6747
  -1.000  -0.1074   0.00878   0.00254  -0.0021   0.8468   0.6921
  -0.750  -0.0796   0.00873   0.00249  -0.0018   0.8257   0.7093
  -0.500  -0.0527   0.00870   0.00245  -0.0013   0.8049   0.7275
  -0.250  -0.0263   0.00868   0.00242  -0.0007   0.7844   0.7460
   0.000   0.0000   0.00868   0.00241   0.0000   0.7649   0.7649
   0.250   0.0263   0.00868   0.00242   0.0007   0.7460   0.7844
   0.500   0.0527   0.00870   0.00245   0.0013   0.7275   0.8049
   0.750   0.0796   0.00873   0.00249   0.0018   0.7094   0.8256
   1.000   0.1074   0.00878   0.00254   0.0021   0.6921   0.8468
   1.250   0.1363   0.00885   0.00262   0.0022   0.6748   0.8680
   1.500   0.1674   0.00893   0.00270   0.0018   0.6558   0.8876
   1.750   0.1998   0.00904   0.00279   0.0012   0.6354   0.9061
   2.000   0.2330   0.00917   0.00288   0.0002   0.6122   0.9228
   2.250   0.2669   0.00932   0.00297  -0.0009   0.5858   0.9374
   2.500   0.3014   0.00948   0.00306  -0.0021   0.5564   0.9504
   2.750   0.3358   0.00966   0.00316  -0.0035   0.5251   0.9620
   3.000   0.3702   0.00985   0.00328  -0.0048   0.4909   0.9730
   3.250   0.4043   0.01008   0.00340  -0.0062   0.4532   0.9832
   3.500   0.4403   0.01035   0.00354  -0.0081   0.4055   0.9917
   3.750   0.4752   0.01075   0.00372  -0.0100   0.3363   1.0000
   4.000   0.4936   0.01135   0.00393  -0.0085   0.2503   1.0000
   4.250   0.5120   0.01207   0.00429  -0.0072   0.1745   1.0000
   4.500   0.5316   0.01271   0.00468  -0.0059   0.1243   1.0000
   4.750   0.5520   0.01327   0.00511  -0.0048   0.0912   1.0000
   5.000   0.5728   0.01381   0.00555  -0.0036   0.0715   1.0000
   5.250   0.5939   0.01434   0.00603  -0.0025   0.0582   1.0000
   5.500   0.6150   0.01488   0.00656  -0.0014   0.0492   1.0000
   5.750   0.6363   0.01541   0.00716  -0.0002   0.0432   1.0000
   6.000   0.6566   0.01606   0.00780   0.0010   0.0378   1.0000
   6.250   0.6775   0.01668   0.00850   0.0022   0.0345   1.0000
   6.500   0.6984   0.01732   0.00921   0.0034   0.0316   1.0000
   6.750   0.7180   0.01813   0.01002   0.0046   0.0286   1.0000
   7.000   0.7384   0.01889   0.01089   0.0058   0.0266   1.0000
   7.250   0.7586   0.01973   0.01182   0.0070   0.0249   1.0000
   7.500   0.7787   0.02060   0.01277   0.0081   0.0234   1.0000
   7.750   0.7983   0.02155   0.01376   0.0092   0.0221   1.0000
   8.000   0.8164   0.02288   0.01515   0.0105   0.0208   1.0000
   8.250   0.8369   0.02382   0.01629   0.0116   0.0195   1.0000
   8.500   0.8561   0.02502   0.01766   0.0127   0.0185   1.0000
   8.750   0.8746   0.02634   0.01914   0.0139   0.0177   1.0000
   9.000   0.8924   0.02769   0.02064   0.0150   0.0170   1.0000
   9.250   0.9090   0.02909   0.02217   0.0162   0.0165   1.0000
   9.500   0.9237   0.03082   0.02406   0.0175   0.0160   1.0000
   9.750   0.9348   0.03318   0.02666   0.0190   0.0155   1.0000
  10.000   0.9441   0.03533   0.02921   0.0208   0.0150   1.0000
  10.250   0.9489   0.03785   0.03211   0.0227   0.0144   1.0000
  10.500   0.9497   0.04045   0.03504   0.0248   0.0139   1.0000
  10.750   0.9441   0.04318   0.03806   0.0273   0.0136   1.0000
  11.000   0.9337   0.04582   0.04094   0.0297   0.0134   1.0000
  11.250   0.9185   0.04921   0.04457   0.0309   0.0133   1.0000
  11.500   0.8981   0.05377   0.04937   0.0302   0.0133   1.0000
  11.750   0.8761   0.05941   0.05523   0.0274   0.0134   1.0000
  12.000   0.8516   0.06657   0.06260   0.0225   0.0133   1.0000
  12.250   0.8172   0.07737   0.07358   0.0144   0.0138   1.0000
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