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NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il)
Reynolds number: 100,000
Max Cl/Cd: 25.48 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20414-il-100000.txt
Download as CSV file: xf-sc20414-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0414 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6707   0.09884   0.09279  -0.0410   1.0000   0.1208
 -11.500  -0.8727   0.06997   0.06319  -0.0543   1.0000   0.0954
 -11.250  -0.8894   0.06579   0.05886  -0.0537   1.0000   0.0952
 -11.000  -0.9043   0.06177   0.05463  -0.0528   1.0000   0.0951
 -10.750  -0.9158   0.05803   0.05061  -0.0515   1.0000   0.0952
 -10.500  -0.9230   0.05454   0.04678  -0.0500   1.0000   0.0954
 -10.250  -0.9225   0.05082   0.04278  -0.0488   1.0000   0.0959
 -10.000  -0.9141   0.04748   0.03930  -0.0478   1.0000   0.0968
  -9.750  -0.9000   0.04512   0.03689  -0.0469   1.0000   0.0981
  -9.500  -0.8854   0.04328   0.03499  -0.0458   1.0000   0.1001
  -9.250  -0.8729   0.04126   0.03277  -0.0447   1.0000   0.1025
  -9.000  -0.8600   0.03908   0.03026  -0.0437   1.0000   0.1048
  -8.750  -0.8453   0.03702   0.02780  -0.0427   1.0000   0.1069
  -8.500  -0.8280   0.03481   0.02541  -0.0418   1.0000   0.1092
  -8.250  -0.8090   0.03343   0.02408  -0.0408   1.0000   0.1125
  -8.000  -0.7896   0.03220   0.02276  -0.0399   1.0000   0.1164
  -7.750  -0.7698   0.03093   0.02120  -0.0390   1.0000   0.1201
  -7.500  -0.7500   0.02941   0.01974  -0.0379   1.0000   0.1240
  -7.250  -0.7299   0.02844   0.01880  -0.0369   1.0000   0.1290
  -7.000  -0.7088   0.02753   0.01769  -0.0360   1.0000   0.1344
  -6.750  -0.6889   0.02634   0.01664  -0.0347   1.0000   0.1399
  -6.500  -0.6681   0.02553   0.01586  -0.0337   1.0000   0.1469
  -6.250  -0.6476   0.02459   0.01496  -0.0326   1.0000   0.1541
  -6.000  -0.6266   0.02385   0.01430  -0.0316   1.0000   0.1632
  -5.750  -0.6060   0.02303   0.01363  -0.0306   1.0000   0.1736
  -5.500  -0.5846   0.02228   0.01300  -0.0298   1.0000   0.1871
  -5.250  -0.5623   0.02150   0.01245  -0.0293   1.0000   0.2056
  -5.000  -0.5385   0.02063   0.01188  -0.0292   1.0000   0.2355
  -4.750  -0.5078   0.01886   0.01102  -0.0318   1.0000   0.3271
  -4.500  -0.4965   0.01911   0.01282  -0.0270   1.0000   0.5404
  -4.250  -0.4787   0.02041   0.01409  -0.0237   1.0000   0.6009
  -4.000  -0.4611   0.02162   0.01522  -0.0207   1.0000   0.6295
  -3.750  -0.4474   0.02285   0.01641  -0.0166   1.0000   0.6474
  -3.500  -0.4320   0.02390   0.01739  -0.0132   1.0000   0.6639
  -3.250  -0.4252   0.02513   0.01864  -0.0071   1.0000   0.6731
  -3.000  -0.4118   0.02599   0.01947  -0.0032   1.0000   0.6867
  -2.750  -0.3956   0.02670   0.02012  -0.0005   1.0000   0.7020
  -2.500  -0.3880   0.02751   0.02095   0.0050   1.0000   0.7120
  -2.250  -0.3744   0.02802   0.02142   0.0083   1.0000   0.7248
  -2.000  -0.3567   0.02840   0.02176   0.0102   1.0000   0.7394
  -1.750  -0.3484   0.02882   0.02219   0.0151   1.0000   0.7500
  -1.500  -0.3362   0.02908   0.02244   0.0185   1.0000   0.7627
  -1.250  -0.3230   0.02931   0.02265   0.0215   1.0000   0.7771
  -1.000  -0.3127   0.02953   0.02288   0.0253   1.0000   0.7932
  -0.750  -0.3026   0.02964   0.02300   0.0291   1.0000   0.8094
  -0.500  -0.2739   0.02987   0.02320   0.0292   0.9946   0.8251
  -0.250  -0.2433   0.02981   0.02312   0.0287   0.9878   0.8340
   0.000  -0.1994   0.02999   0.02326   0.0241   0.9816   0.8411
   0.250  -0.1683   0.02976   0.02302   0.0232   0.9729   0.8467
   0.500  -0.1257   0.02981   0.02306   0.0195   0.9628   0.8535
   0.750  -0.0779   0.02982   0.02306   0.0150   0.9537   0.8587
   1.000  -0.0426   0.02957   0.02283   0.0129   0.9420   0.8617
   1.250  -0.0038   0.02944   0.02272   0.0102   0.9308   0.8652
   1.500   0.0457   0.02925   0.02256   0.0058   0.9184   0.8684
   1.750   0.1025   0.02879   0.02214   0.0006   0.9022   0.8710
   2.000   0.1618   0.02795   0.02136  -0.0042   0.8863   0.8736
   2.250   0.2180   0.02683   0.02032  -0.0077   0.8704   0.8763
   2.500   0.2703   0.02569   0.01928  -0.0106   0.8539   0.8790
   2.750   0.3173   0.02456   0.01823  -0.0126   0.8368   0.8811
   3.000   0.3598   0.02352   0.01728  -0.0140   0.8191   0.8828
   3.250   0.4034   0.02233   0.01617  -0.0152   0.7973   0.8846
   3.500   0.4336   0.02152   0.01543  -0.0146   0.7658   0.8871
   3.750   0.4653   0.02055   0.01444  -0.0136   0.7212   0.8894
   4.000   0.4886   0.01990   0.01361  -0.0113   0.6322   0.8914
   4.250   0.5011   0.02059   0.01303  -0.0074   0.4162   0.8932
   4.500   0.5111   0.02191   0.01346  -0.0049   0.2989   0.8953
   4.750   0.5304   0.02285   0.01395  -0.0041   0.2484   0.8974
   5.000   0.5539   0.02369   0.01447  -0.0040   0.2198   0.9000
   5.250   0.5812   0.02449   0.01513  -0.0045   0.1990   0.9026
   5.500   0.6056   0.02510   0.01561  -0.0042   0.1843   0.9050
   5.750   0.6329   0.02593   0.01625  -0.0045   0.1720   0.9072
   6.000   0.6601   0.02653   0.01692  -0.0047   0.1611   0.9100
   6.250   0.6897   0.02754   0.01789  -0.0054   0.1524   0.9130
   6.500   0.7194   0.02841   0.01874  -0.0063   0.1440   0.9156
   6.750   0.7491   0.02961   0.01998  -0.0071   0.1375   0.9177
   7.000   0.7751   0.03042   0.02090  -0.0070   0.1312   0.9202
   7.250   0.8045   0.03197   0.02229  -0.0079   0.1257   0.9226
   7.500   0.8293   0.03302   0.02372  -0.0077   0.1213   0.9256
   7.750   0.8561   0.03421   0.02503  -0.0080   0.1165   0.9289
   8.000   0.8834   0.03586   0.02662  -0.0087   0.1126   0.9320
   8.250   0.9030   0.03763   0.02880  -0.0078   0.1100   0.9353
   8.500   0.9224   0.03946   0.03106  -0.0070   0.1070   0.9384
   8.750   0.9439   0.04119   0.03300  -0.0068   0.1038   0.9415
   9.000   0.9695   0.04291   0.03471  -0.0074   0.1011   0.9445
   9.250   0.9882   0.04603   0.03796  -0.0073   0.0995   0.9479
   9.500   0.9955   0.04882   0.04127  -0.0053   0.0987   0.9520
   9.750   0.9988   0.05210   0.04510  -0.0034   0.0978   0.9563
  10.000   0.9970   0.05567   0.04914  -0.0013   0.0971   0.9610
  10.250   0.9902   0.05972   0.05362   0.0007   0.0968   0.9660
  10.500   0.9795   0.06420   0.05847   0.0023   0.0972   0.9710
  10.750   0.9685   0.06873   0.06327   0.0035   0.0980   0.9770
  11.000   0.9643   0.07343   0.06811   0.0037   0.0988   0.9862
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