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S1048 14% (Danny Howell) (s1048-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S1048 14% (Danny Howell) (s1048-il)
Reynolds number: 50,000
Max Cl/Cd: 24.17 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1048-il-50000.txt
Download as CSV file: xf-s1048-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1048 14% (Danny Howell)                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6520   0.13404   0.12683   0.0053   1.0000   0.1594
 -12.750  -0.6545   0.12779   0.12061   0.0030   1.0000   0.1589
 -12.500  -0.6626   0.12085   0.11373   0.0001   1.0000   0.1587
 -12.250  -0.8165   0.08369   0.07687  -0.0267   1.0000   0.1175
 -12.000  -0.8454   0.07622   0.06933  -0.0304   1.0000   0.1161
 -11.750  -0.8752   0.06978   0.06276  -0.0329   1.0000   0.1144
 -11.500  -0.9048   0.06441   0.05721  -0.0338   1.0000   0.1132
 -11.250  -0.9301   0.06016   0.05273  -0.0328   1.0000   0.1133
 -11.000  -0.9497   0.05651   0.04881  -0.0305   1.0000   0.1144
 -10.750  -0.9654   0.05288   0.04477  -0.0282   1.0000   0.1167
 -10.500  -0.9551   0.05010   0.04203  -0.0270   1.0000   0.1248
 -10.250  -0.9612   0.04684   0.03831  -0.0244   1.0000   0.1309
 -10.000  -0.9496   0.04424   0.03574  -0.0229   1.0000   0.1433
  -9.750  -0.9434   0.04181   0.03317  -0.0207   1.0000   0.1584
  -9.500  -0.9297   0.04003   0.03169  -0.0188   1.0000   0.1805
  -9.250  -0.9225   0.03838   0.03010  -0.0163   1.0000   0.2055
  -9.000  -0.9102   0.03765   0.02962  -0.0137   1.0000   0.2362
  -8.750  -0.8949   0.03748   0.02965  -0.0110   1.0000   0.2687
  -8.500  -0.8772   0.03748   0.02976  -0.0084   1.0000   0.3000
  -8.250  -0.8548   0.03776   0.03011  -0.0061   1.0000   0.3292
  -8.000  -0.8297   0.03819   0.03059  -0.0038   1.0000   0.3560
  -7.750  -0.8173   0.03735   0.02961  -0.0014   1.0000   0.3794
  -7.500  -0.7819   0.03857   0.03090   0.0006   1.0000   0.4031
  -7.250  -0.7739   0.03715   0.02930   0.0030   1.0000   0.4236
  -7.000  -0.7384   0.03815   0.03032   0.0049   1.0000   0.4432
  -6.750  -0.7147   0.03811   0.03020   0.0070   1.0000   0.4620
  -6.500  -0.6987   0.03732   0.02932   0.0091   1.0000   0.4801
  -6.250  -0.6876   0.03619   0.02807   0.0113   1.0000   0.4982
  -6.000  -0.6678   0.03576   0.02756   0.0134   1.0000   0.5149
  -5.750  -0.6468   0.03546   0.02721   0.0156   1.0000   0.5309
  -5.500  -0.6283   0.03499   0.02669   0.0178   1.0000   0.5467
  -5.250  -0.6117   0.03442   0.02607   0.0200   1.0000   0.5622
  -5.000  -0.5967   0.03379   0.02540   0.0224   1.0000   0.5775
  -4.750  -0.5836   0.03312   0.02468   0.0248   1.0000   0.5926
  -4.500  -0.5723   0.03246   0.02399   0.0275   1.0000   0.6076
  -4.250  -0.5630   0.03178   0.02327   0.0302   1.0000   0.6224
  -4.000  -0.5549   0.03112   0.02258   0.0331   1.0000   0.6372
  -3.750  -0.5475   0.03049   0.02192   0.0360   1.0000   0.6520
  -3.500  -0.5397   0.02993   0.02131   0.0387   1.0000   0.6670
  -3.250  -0.5314   0.02940   0.02075   0.0413   1.0000   0.6821
  -3.000  -0.5224   0.02894   0.02027   0.0438   1.0000   0.6975
  -2.750  -0.5126   0.02854   0.01984   0.0462   1.0000   0.7131
  -2.500  -0.5020   0.02821   0.01949   0.0485   1.0000   0.7291
  -2.250  -0.4911   0.02790   0.01915   0.0506   1.0000   0.7454
  -2.000  -0.4797   0.02764   0.01887   0.0526   1.0000   0.7624
  -1.750  -0.4679   0.02739   0.01861   0.0544   1.0000   0.7801
  -1.500  -0.4563   0.02714   0.01834   0.0561   1.0000   0.7992
  -1.250  -0.4313   0.02718   0.01833   0.0553   0.9955   0.8198
  -1.000  -0.3659   0.02806   0.01915   0.0481   0.9792   0.8408
  -0.750  -0.3019   0.02872   0.01972   0.0408   0.9626   0.8631
  -0.500  -0.2164   0.02958   0.02053   0.0300   0.9464   0.8819
  -0.250  -0.1153   0.03030   0.02118   0.0163   0.9304   0.8989
   0.000   0.0001   0.03058   0.02144   0.0000   0.9146   0.9146
   0.250   0.1161   0.03029   0.02117  -0.0165   0.8989   0.9304
   0.500   0.2163   0.02958   0.02052  -0.0299   0.8818   0.9463
   0.750   0.3017   0.02872   0.01972  -0.0407   0.8631   0.9625
   1.000   0.3659   0.02807   0.01916  -0.0481   0.8410   0.9792
   1.250   0.4314   0.02718   0.01833  -0.0554   0.8199   0.9956
   1.500   0.4562   0.02714   0.01834  -0.0561   0.7992   1.0000
   1.750   0.4679   0.02739   0.01861  -0.0544   0.7802   1.0000
   2.000   0.4796   0.02764   0.01887  -0.0526   0.7625   1.0000
   2.250   0.4910   0.02791   0.01915  -0.0506   0.7455   1.0000
   2.500   0.5021   0.02820   0.01948  -0.0484   0.7291   1.0000
   2.750   0.5125   0.02854   0.01984  -0.0462   0.7131   1.0000
   3.000   0.5224   0.02894   0.02026  -0.0438   0.6975   1.0000
   3.250   0.5314   0.02940   0.02075  -0.0413   0.6821   1.0000
   3.500   0.5396   0.02992   0.02130  -0.0387   0.6670   1.0000
   3.750   0.5474   0.03049   0.02192  -0.0359   0.6520   1.0000
   4.000   0.5549   0.03111   0.02258  -0.0331   0.6372   1.0000
   4.250   0.5631   0.03176   0.02325  -0.0302   0.6223   1.0000
   4.500   0.5724   0.03245   0.02397  -0.0274   0.6075   1.0000
   4.750   0.5835   0.03313   0.02468  -0.0248   0.5926   1.0000
   5.000   0.5968   0.03379   0.02540  -0.0224   0.5775   1.0000
   5.250   0.6117   0.03441   0.02607  -0.0200   0.5622   1.0000
   5.500   0.6283   0.03498   0.02668  -0.0178   0.5467   1.0000
   5.750   0.6469   0.03544   0.02720  -0.0156   0.5309   1.0000
   6.000   0.6680   0.03573   0.02753  -0.0134   0.5149   1.0000
   6.250   0.6876   0.03618   0.02806  -0.0113   0.4982   1.0000
   6.500   0.6988   0.03732   0.02931  -0.0091   0.4801   1.0000
   6.750   0.7147   0.03810   0.03019  -0.0070   0.4620   1.0000
   7.000   0.7382   0.03818   0.03034  -0.0049   0.4432   1.0000
   7.250   0.7740   0.03715   0.02930  -0.0030   0.4236   1.0000
   7.500   0.7819   0.03857   0.03091  -0.0006   0.4030   1.0000
   7.750   0.8171   0.03738   0.02964   0.0014   0.3795   1.0000
   8.000   0.8300   0.03816   0.03055   0.0038   0.3557   1.0000
   8.250   0.8548   0.03776   0.03011   0.0061   0.3292   1.0000
   8.500   0.8772   0.03748   0.02976   0.0084   0.2999   1.0000
   8.750   0.8950   0.03748   0.02964   0.0110   0.2687   1.0000
   9.000   0.9101   0.03766   0.02963   0.0137   0.2363   1.0000
   9.250   0.9225   0.03838   0.03011   0.0163   0.2055   1.0000
   9.500   0.9298   0.04005   0.03170   0.0188   0.1804   1.0000
   9.750   0.9434   0.04181   0.03318   0.0207   0.1584   1.0000
  10.000   0.9499   0.04426   0.03575   0.0229   0.1434   1.0000
  10.250   0.9615   0.04684   0.03831   0.0244   0.1310   1.0000
  10.500   0.9552   0.05009   0.04202   0.0269   0.1248   1.0000
  10.750   0.9652   0.05288   0.04477   0.0282   0.1167   1.0000
  11.000   0.9495   0.05651   0.04880   0.0305   0.1143   1.0000
  11.250   0.9299   0.06018   0.05275   0.0327   0.1132   1.0000
  11.500   0.9050   0.06445   0.05725   0.0337   0.1133   1.0000
  11.750   0.8755   0.06979   0.06278   0.0328   0.1144   1.0000
  12.000   0.8443   0.07639   0.06951   0.0302   0.1160   1.0000
  12.250   0.8172   0.08371   0.07688   0.0266   0.1175   1.0000
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