Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il)
Reynolds number: 1,000,000
Max Cl/Cd: 78.82 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20414-il-1000000-n5.txt
Download as CSV file: xf-sc20414-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.3443   0.08572   0.08180  -0.0361   1.0000   0.0190
 -19.500  -1.3587   0.07982   0.07577  -0.0390   1.0000   0.0191
 -19.250  -1.3696   0.07463   0.07046  -0.0415   1.0000   0.0192
 -19.000  -1.3772   0.07003   0.06575  -0.0435   1.0000   0.0193
 -18.750  -1.3820   0.06594   0.06155  -0.0453   1.0000   0.0193
 -18.500  -1.3873   0.06193   0.05745  -0.0468   1.0000   0.0195
 -18.250  -1.3927   0.05800   0.05342  -0.0483   1.0000   0.0197
 -18.000  -1.3954   0.05455   0.04989  -0.0494   1.0000   0.0199
 -17.750  -1.3955   0.05154   0.04680  -0.0502   1.0000   0.0200
 -17.500  -1.3936   0.04884   0.04403  -0.0508   1.0000   0.0202
 -17.250  -1.3901   0.04637   0.04150  -0.0513   1.0000   0.0204
 -17.000  -1.3855   0.04410   0.03916  -0.0517   1.0000   0.0206
 -16.750  -1.3794   0.04207   0.03707  -0.0519   1.0000   0.0208
 -16.500  -1.3724   0.04016   0.03509  -0.0520   1.0000   0.0211
 -16.250  -1.3645   0.03839   0.03327  -0.0520   1.0000   0.0213
 -16.000  -1.3561   0.03675   0.03157  -0.0519   1.0000   0.0215
 -15.750  -1.3470   0.03520   0.02997  -0.0518   1.0000   0.0218
 -15.500  -1.3367   0.03379   0.02850  -0.0515   1.0000   0.0220
 -15.250  -1.3261   0.03243   0.02708  -0.0513   1.0000   0.0222
 -15.000  -1.3142   0.03118   0.02578  -0.0510   1.0000   0.0225
 -14.750  -1.3019   0.02999   0.02453  -0.0507   1.0000   0.0227
 -14.500  -1.2892   0.02885   0.02335  -0.0503   1.0000   0.0229
 -14.250  -1.2776   0.02762   0.02208  -0.0499   1.0000   0.0233
 -14.000  -1.2647   0.02652   0.02095  -0.0494   1.0000   0.0236
 -13.750  -1.2508   0.02553   0.01993  -0.0489   1.0000   0.0240
 -13.500  -1.2365   0.02459   0.01897  -0.0483   1.0000   0.0244
 -13.250  -1.2217   0.02374   0.01809  -0.0477   1.0000   0.0249
 -13.000  -1.2071   0.02292   0.01724  -0.0470   1.0000   0.0254
 -12.750  -1.1930   0.02215   0.01645  -0.0460   1.0000   0.0258
 -12.500  -1.1809   0.02144   0.01570  -0.0446   1.0000   0.0261
 -12.250  -1.1740   0.02078   0.01501  -0.0421   1.0000   0.0264
 -12.000  -1.1644   0.02009   0.01431  -0.0402   1.0000   0.0268
 -11.750  -1.1526   0.01941   0.01361  -0.0386   1.0000   0.0273
 -11.500  -1.1323   0.01875   0.01295  -0.0386   0.9994   0.0280
 -11.250  -1.1032   0.01811   0.01230  -0.0401   0.9979   0.0287
 -11.000  -1.0734   0.01752   0.01168  -0.0417   0.9963   0.0295
 -10.750  -1.0427   0.01696   0.01111  -0.0434   0.9947   0.0302
 -10.500  -1.0112   0.01641   0.01054  -0.0452   0.9934   0.0311
 -10.250  -0.9803   0.01586   0.01000  -0.0469   0.9917   0.0323
 -10.000  -0.9497   0.01536   0.00950  -0.0484   0.9895   0.0335
  -9.750  -0.9180   0.01491   0.00904  -0.0500   0.9874   0.0345
  -9.500  -0.8855   0.01447   0.00859  -0.0517   0.9856   0.0355
  -9.250  -0.8528   0.01401   0.00814  -0.0535   0.9837   0.0369
  -9.000  -0.8195   0.01361   0.00774  -0.0552   0.9819   0.0383
  -8.750  -0.7880   0.01326   0.00738  -0.0565   0.9791   0.0397
  -8.500  -0.7580   0.01290   0.00703  -0.0575   0.9751   0.0411
  -8.250  -0.7265   0.01255   0.00669  -0.0588   0.9717   0.0430
  -8.000  -0.6942   0.01223   0.00638  -0.0601   0.9686   0.0447
  -7.750  -0.6637   0.01194   0.00608  -0.0610   0.9638   0.0462
  -7.500  -0.6330   0.01162   0.00578  -0.0620   0.9583   0.0483
  -7.000  -0.5718   0.01109   0.00526  -0.0638   0.9475   0.0527
  -6.750  -0.5414   0.01082   0.00501  -0.0646   0.9417   0.0555
  -6.500  -0.5111   0.01060   0.00478  -0.0653   0.9362   0.0580
  -6.250  -0.4809   0.01037   0.00455  -0.0660   0.9296   0.0607
  -6.000  -0.4506   0.01014   0.00434  -0.0667   0.9231   0.0642
  -5.750  -0.4203   0.00993   0.00414  -0.0674   0.9166   0.0682
  -5.500  -0.3898   0.00972   0.00395  -0.0681   0.9100   0.0732
  -5.250  -0.3592   0.00952   0.00376  -0.0689   0.9041   0.0791
  -5.000  -0.3284   0.00933   0.00359  -0.0697   0.8974   0.0856
  -4.750  -0.2976   0.00913   0.00342  -0.0704   0.8901   0.0939
  -4.500  -0.2666   0.00893   0.00326  -0.0712   0.8835   0.1024
  -4.250  -0.2355   0.00875   0.00311  -0.0720   0.8765   0.1125
  -3.750  -0.1726   0.00836   0.00282  -0.0738   0.8621   0.1428
  -3.500  -0.1410   0.00816   0.00268  -0.0748   0.8542   0.1627
  -3.250  -0.1085   0.00790   0.00253  -0.0760   0.8472   0.1945
  -3.000  -0.0757   0.00762   0.00238  -0.0773   0.8389   0.2325
  -2.750  -0.0421   0.00730   0.00222  -0.0789   0.8292   0.2827
  -2.500  -0.0071   0.00685   0.00201  -0.0809   0.8138   0.3604
  -2.250   0.0281   0.00644   0.00181  -0.0829   0.7974   0.4368
  -2.000   0.0631   0.00608   0.00169  -0.0847   0.7820   0.5154
  -1.750   0.0946   0.00603   0.00168  -0.0855   0.7633   0.5496
  -1.500   0.1248   0.00609   0.00168  -0.0858   0.7404   0.5687
  -1.250   0.1550   0.00615   0.00169  -0.0862   0.7164   0.5837
  -1.000   0.1849   0.00624   0.00171  -0.0864   0.6896   0.5947
  -0.750   0.2140   0.00643   0.00175  -0.0866   0.6468   0.6040
  -0.500   0.2430   0.00665   0.00179  -0.0867   0.6007   0.6116
  -0.250   0.2704   0.00711   0.00193  -0.0866   0.5124   0.6195
   0.000   0.2980   0.00758   0.00208  -0.0867   0.4282   0.6254
   0.250   0.3258   0.00801   0.00221  -0.0867   0.3560   0.6293
   0.500   0.3539   0.00838   0.00236  -0.0868   0.2942   0.6326
   0.750   0.3822   0.00872   0.00249  -0.0869   0.2435   0.6357
   1.000   0.4106   0.00902   0.00261  -0.0870   0.2044   0.6389
   1.250   0.4393   0.00928   0.00273  -0.0871   0.1739   0.6416
   1.500   0.4683   0.00948   0.00283  -0.0873   0.1543   0.6434
   1.750   0.4973   0.00968   0.00294  -0.0874   0.1370   0.6448
   2.000   0.5261   0.00987   0.00305  -0.0876   0.1219   0.6463
   2.250   0.5550   0.01005   0.00318  -0.0877   0.1102   0.6480
   2.750   0.6126   0.01040   0.00344  -0.0879   0.0920   0.6512
   3.000   0.6414   0.01058   0.00358  -0.0880   0.0860   0.6528
   3.250   0.6701   0.01075   0.00373  -0.0881   0.0813   0.6545
   3.500   0.6987   0.01093   0.00388  -0.0881   0.0770   0.6561
   3.750   0.7274   0.01110   0.00403  -0.0882   0.0728   0.6577
   4.000   0.7558   0.01130   0.00420  -0.0882   0.0684   0.6594
   4.250   0.7842   0.01149   0.00436  -0.0882   0.0648   0.6610
   4.500   0.8124   0.01170   0.00453  -0.0882   0.0610   0.6624
   4.750   0.8406   0.01189   0.00471  -0.0882   0.0579   0.6641
   5.000   0.8685   0.01211   0.00491  -0.0881   0.0546   0.6661
   5.250   0.8965   0.01231   0.00512  -0.0880   0.0525   0.6681
   5.500   0.9243   0.01253   0.00534  -0.0879   0.0502   0.6699
   5.750   0.9517   0.01278   0.00557  -0.0878   0.0480   0.6717
   6.000   0.9794   0.01300   0.00580  -0.0877   0.0464   0.6733
   6.250   1.0067   0.01324   0.00603  -0.0875   0.0445   0.6750
   6.500   1.0337   0.01351   0.00629  -0.0873   0.0426   0.6767
   6.750   1.0608   0.01376   0.00655  -0.0871   0.0413   0.6784
   7.000   1.0878   0.01402   0.00681  -0.0868   0.0400   0.6800
   7.500   1.1408   0.01460   0.00739  -0.0862   0.0372   0.6835
   7.750   1.1673   0.01488   0.00769  -0.0859   0.0362   0.6853
   8.000   1.1935   0.01516   0.00800  -0.0856   0.0350   0.6870
   8.250   1.2194   0.01547   0.00831  -0.0852   0.0338   0.6888
   8.500   1.2448   0.01582   0.00866  -0.0847   0.0327   0.6907
   8.750   1.2702   0.01615   0.00902  -0.0842   0.0319   0.6925
   9.000   1.2956   0.01648   0.00937  -0.0837   0.0311   0.6944
   9.250   1.3205   0.01683   0.00974  -0.0832   0.0303   0.6961
   9.500   1.3451   0.01719   0.01011  -0.0826   0.0295   0.6978
   9.750   1.3692   0.01759   0.01052  -0.0819   0.0287   0.6992
  10.000   1.3927   0.01804   0.01097  -0.0811   0.0279   0.7007
  10.250   1.4167   0.01840   0.01139  -0.0804   0.0274   0.7029
  10.500   1.4401   0.01879   0.01182  -0.0797   0.0268   0.7051
  10.750   1.4630   0.01921   0.01228  -0.0788   0.0262   0.7072
  11.000   1.4853   0.01966   0.01276  -0.0779   0.0257   0.7094
  11.250   1.5070   0.02013   0.01326  -0.0769   0.0252   0.7114
  11.500   1.5280   0.02065   0.01380  -0.0758   0.0247   0.7134
  11.750   1.5478   0.02122   0.01441  -0.0745   0.0242   0.7153
  12.000   1.5678   0.02173   0.01496  -0.0732   0.0239   0.7171
  12.250   1.5870   0.02224   0.01552  -0.0718   0.0236   0.7187
  12.500   1.6050   0.02278   0.01612  -0.0702   0.0233   0.7206
  12.750   1.6216   0.02334   0.01675  -0.0684   0.0230   0.7227
  13.000   1.6349   0.02392   0.01739  -0.0660   0.0227   0.7249
  13.250   1.6478   0.02457   0.01810  -0.0637   0.0224   0.7271
  13.500   1.6613   0.02529   0.01887  -0.0616   0.0221   0.7293
  13.750   1.6744   0.02605   0.01969  -0.0595   0.0218   0.7316
  14.000   1.6868   0.02689   0.02058  -0.0575   0.0215   0.7338
  14.250   1.6982   0.02782   0.02156  -0.0554   0.0212   0.7360
  14.500   1.7083   0.02887   0.02266  -0.0533   0.0209   0.7378
  14.750   1.7172   0.03002   0.02389  -0.0512   0.0205   0.7401
  15.000   1.7276   0.03108   0.02504  -0.0494   0.0204   0.7427
  15.250   1.7375   0.03223   0.02628  -0.0477   0.0203   0.7454
  15.500   1.7462   0.03349   0.02763  -0.0460   0.0201   0.7481
  15.750   1.7541   0.03488   0.02910  -0.0443   0.0199   0.7506
  16.000   1.7611   0.03638   0.03068  -0.0428   0.0198   0.7529
  16.250   1.7670   0.03802   0.03240  -0.0413   0.0196   0.7549
  16.500   1.7721   0.03979   0.03427  -0.0400   0.0194   0.7569
  16.750   1.7760   0.04174   0.03632  -0.0388   0.0193   0.7592
  17.000   1.7786   0.04389   0.03857  -0.0378   0.0191   0.7615
  17.250   1.7797   0.04625   0.04103  -0.0369   0.0190   0.7638
  17.500   1.7794   0.04888   0.04376  -0.0363   0.0188   0.7661
  17.750   1.7776   0.05177   0.04675  -0.0358   0.0187   0.7684
  18.000   1.7736   0.05504   0.05013  -0.0357   0.0186   0.7705
  18.250   1.7678   0.05871   0.05391  -0.0359   0.0184   0.7724
  18.500   1.7596   0.06291   0.05824  -0.0367   0.0183   0.7743
  18.750   1.7487   0.06773   0.06319  -0.0380   0.0182   0.7764
  19.000   1.7340   0.07336   0.06897  -0.0399   0.0181   0.7784
  19.250   1.7147   0.08009   0.07586  -0.0428   0.0181   0.7802
<< Back to NASA SC(2)-0414 AIRFOIL (sc20414-il)

Polar data table (+)

Polar graphs


<< Back to NASA SC(2)-0414 AIRFOIL (sc20414-il)