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NREL's S815 Airfoil (s815-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S815 Airfoil (s815-nr)
Reynolds number: 200,000
Max Cl/Cd: 54.79 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s815-nr-200000-n5.txt
Download as CSV file: xf-s815-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S815 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1475   0.10475   0.09877  -0.0582   0.9714   0.2543
  -9.000  -0.1244   0.10284   0.09685  -0.0607   0.9681   0.2555
  -8.500  -0.1370   0.09401   0.08790  -0.0656   0.9588   0.2645
  -8.250  -0.1118   0.09273   0.08663  -0.0670   0.9536   0.2649
  -8.000  -0.0832   0.09122   0.08513  -0.0695   0.9500   0.2653
  -7.750  -0.0708   0.09034   0.08429  -0.0680   0.9384   0.2658
  -7.250  -0.0463   0.08843   0.08244  -0.0656   0.9073   0.2669
  -7.000  -0.0266   0.08704   0.08105  -0.0662   0.8911   0.2677
  -6.750   0.0038   0.08528   0.07927  -0.0692   0.8759   0.2689
  -6.500   0.0418   0.08274   0.07667  -0.0746   0.8619   0.2703
  -6.000   0.0778   0.07032   0.06387  -0.0935   0.8321   0.2787
  -5.750   0.1557   0.06760   0.06095  -0.1067   0.8045   0.2792
  -5.500   0.2057   0.06584   0.05895  -0.1137   0.7693   0.2796
  -5.250   0.2333   0.06489   0.05781  -0.1156   0.7379   0.2801
  -3.750  -0.1298   0.02434   0.01594  -0.1086   0.6579   0.3092
  -3.500  -0.1098   0.02386   0.01541  -0.1083   0.6454   0.3099
  -3.250  -0.0886   0.02347   0.01495  -0.1082   0.6340   0.3105
  -3.000  -0.0670   0.02312   0.01455  -0.1080   0.6225   0.3111
  -2.750  -0.0446   0.02280   0.01417  -0.1079   0.6121   0.3117
  -2.500  -0.0218   0.02248   0.01381  -0.1078   0.6018   0.3124
  -2.250   0.0019   0.02218   0.01344  -0.1080   0.5929   0.3131
  -2.000   0.0261   0.02187   0.01310  -0.1081   0.5841   0.3139
  -1.500   0.0768   0.02127   0.01240  -0.1088   0.5692   0.3155
  -1.250   0.1029   0.02099   0.01207  -0.1093   0.5622   0.3164
  -1.000   0.1300   0.02074   0.01173  -0.1099   0.5562   0.3174
  -0.750   0.1573   0.02044   0.01142  -0.1105   0.5501   0.3184
  -0.500   0.1850   0.02018   0.01111  -0.1112   0.5442   0.3194
  -0.250   0.2134   0.01996   0.01081  -0.1119   0.5390   0.3205
   0.000   0.2424   0.01974   0.01054  -0.1127   0.5341   0.3216
   0.250   0.2712   0.01952   0.01028  -0.1135   0.5287   0.3228
   0.500   0.3005   0.01935   0.01004  -0.1143   0.5236   0.3239
   0.750   0.3300   0.01923   0.00986  -0.1150   0.5193   0.3251
   1.000   0.3584   0.01917   0.00984  -0.1154   0.5156   0.3262
   1.250   0.3866   0.01911   0.00986  -0.1157   0.5117   0.3272
   1.500   0.4152   0.01909   0.00988  -0.1160   0.5078   0.3283
   1.750   0.4442   0.01907   0.00989  -0.1164   0.5043   0.3293
   2.000   0.4737   0.01907   0.00989  -0.1170   0.5010   0.3305
   2.250   0.5043   0.01910   0.00990  -0.1177   0.4982   0.3317
   2.500   0.5333   0.01908   0.00994  -0.1182   0.4950   0.3330
   2.750   0.5623   0.01906   0.00997  -0.1186   0.4915   0.3344
   3.000   0.5914   0.01905   0.00998  -0.1190   0.4881   0.3359
   3.250   0.6213   0.01906   0.01000  -0.1196   0.4851   0.3374
   3.500   0.6519   0.01909   0.01002  -0.1203   0.4825   0.3389
   3.750   0.6834   0.01914   0.01004  -0.1212   0.4801   0.3405
   4.000   0.7142   0.01921   0.01014  -0.1219   0.4778   0.3419
   4.250   0.7420   0.01927   0.01033  -0.1220   0.4752   0.3434
   4.500   0.7699   0.01935   0.01052  -0.1221   0.4722   0.3449
   4.750   0.7981   0.01944   0.01070  -0.1222   0.4692   0.3465
   5.000   0.8269   0.01955   0.01088  -0.1225   0.4666   0.3483
   5.250   0.8558   0.01967   0.01104  -0.1228   0.4638   0.3504
   5.500   0.8861   0.01981   0.01117  -0.1233   0.4605   0.3527
   5.750   0.9138   0.01993   0.01135  -0.1234   0.4571   0.3551
   6.000   0.9396   0.02004   0.01153  -0.1231   0.4534   0.3574
   6.250   0.9650   0.02013   0.01174  -0.1227   0.4493   0.3594
   6.500   0.9904   0.02022   0.01192  -0.1222   0.4450   0.3615
   6.750   1.0189   0.02037   0.01206  -0.1223   0.4405   0.3636
   7.000   1.0387   0.02047   0.01232  -0.1209   0.4351   0.3658
   7.250   1.0592   0.02055   0.01249  -0.1196   0.4291   0.3682
   7.500   1.0816   0.02064   0.01258  -0.1186   0.4234   0.3707
   7.750   1.1007   0.02076   0.01276  -0.1170   0.4174   0.3732
   8.000   1.1179   0.02087   0.01296  -0.1152   0.4105   0.3755
   8.250   1.1378   0.02102   0.01315  -0.1138   0.4041   0.3778
   8.500   1.1559   0.02124   0.01352  -0.1122   0.3972   0.3801
   8.750   1.1735   0.02147   0.01386  -0.1105   0.3894   0.3826
   9.000   1.1911   0.02174   0.01417  -0.1088   0.3818   0.3854
   9.250   1.2071   0.02204   0.01458  -0.1070   0.3721   0.3884
   9.500   1.2223   0.02239   0.01497  -0.1051   0.3619   0.3915
   9.750   1.2352   0.02280   0.01542  -0.1029   0.3488   0.3942
  10.000   1.2463   0.02331   0.01601  -0.1006   0.3319   0.3968
  10.250   1.2536   0.02401   0.01671  -0.0978   0.3098   0.3995
  10.500   1.2539   0.02509   0.01768  -0.0945   0.2841   0.4021
  10.750   1.2498   0.02654   0.01902  -0.0909   0.2605   0.4045
  11.000   1.2461   0.02820   0.02059  -0.0878   0.2386   0.4070
  11.250   1.2415   0.03009   0.02241  -0.0850   0.2188   0.4094
  11.500   1.2367   0.03219   0.02445  -0.0826   0.2011   0.4115
  11.750   1.2319   0.03448   0.02675  -0.0806   0.1850   0.4134
  12.000   1.2270   0.03698   0.02925  -0.0790   0.1704   0.4155
  12.250   1.2224   0.03966   0.03194  -0.0778   0.1575   0.4176
  12.500   1.2173   0.04256   0.03485  -0.0768   0.1458   0.4199
  12.750   1.2125   0.04560   0.03790  -0.0761   0.1350   0.4223
  13.000   1.2098   0.04860   0.04093  -0.0758   0.1251   0.4248
  13.250   1.2062   0.05182   0.04416  -0.0756   0.1164   0.4273
  13.500   1.2024   0.05518   0.04752  -0.0756   0.1083   0.4298
  13.750   1.2013   0.05835   0.05076  -0.0757   0.1007   0.4322
  14.000   1.1987   0.06178   0.05424  -0.0760   0.0942   0.4347
  14.250   1.1980   0.06507   0.05758  -0.0763   0.0879   0.4376
  14.500   1.1973   0.06844   0.06100  -0.0768   0.0824   0.4406
  14.750   1.1973   0.07181   0.06440  -0.0773   0.0772   0.4439
  15.000   1.1980   0.07516   0.06779  -0.0780   0.0726   0.4473
  15.250   1.1986   0.07858   0.07125  -0.0787   0.0682   0.4502
  15.500   1.2001   0.08192   0.07468  -0.0795   0.0644   0.4532
  15.750   1.2018   0.08533   0.07815  -0.0803   0.0607   0.4564
  16.000   1.2031   0.08879   0.08168  -0.0812   0.0575   0.4599
  16.250   1.2059   0.09213   0.08507  -0.0821   0.0543   0.4638
  16.750   1.2103   0.09902   0.09210  -0.0842   0.0490   0.4711
  17.000   1.2126   0.10250   0.09565  -0.0854   0.0466   0.4748
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