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NACA 2-H-15 AIRFOIL (n2h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 2-H-15 AIRFOIL (n2h15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 145.11 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n2h15-il-1000000.txt
Download as CSV file: xf-n2h15-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2-H-15 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1135   0.09115   0.08809  -0.0902   0.6925   0.0228
 -10.750  -0.1144   0.08763   0.08457  -0.0919   0.6917   0.0228
 -10.500  -0.1128   0.08458   0.08152  -0.0932   0.6909   0.0229
 -10.250  -0.1129   0.08133   0.07827  -0.0945   0.6901   0.0229
 -10.000  -0.1139   0.07808   0.07504  -0.0958   0.6890   0.0229
  -9.750  -0.1184   0.07440   0.07136  -0.0974   0.6879   0.0229
  -9.500  -0.1341   0.06969   0.06668  -0.0986   0.6867   0.0232
  -9.250  -0.1468   0.06605   0.06306  -0.1007   0.6857   0.0232
  -9.000  -0.1578   0.06340   0.06043  -0.1006   0.6851   0.0233
  -8.750  -0.1728   0.06062   0.05765  -0.0990   0.6842   0.0233
  -8.500  -0.1878   0.05819   0.05521  -0.0963   0.6833   0.0234
  -8.250  -0.2006   0.05625   0.05326  -0.0927   0.6822   0.0234
  -8.000  -0.2120   0.05466   0.05165  -0.0884   0.6811   0.0235
  -7.750  -0.2288   0.05296   0.04992  -0.0830   0.6800   0.0236
  -7.500  -0.2346   0.05133   0.04825  -0.0793   0.6788   0.0237
  -7.250  -0.2387   0.04948   0.04635  -0.0758   0.6777   0.0238
  -7.000  -0.2392   0.04786   0.04467  -0.0725   0.6766   0.0241
  -6.750  -0.2376   0.04623   0.04298  -0.0694   0.6757   0.0244
  -6.500  -0.2387   0.04406   0.04071  -0.0656   0.6747   0.0245
  -6.250  -0.2367   0.04214   0.03869  -0.0621   0.6737   0.0251
  -6.000  -0.2394   0.03824   0.03441  -0.0557   0.6726   0.0272
  -5.750  -0.2393   0.03624   0.03220  -0.0509   0.6711   0.0273
  -5.500  -0.2356   0.03441   0.03021  -0.0467   0.6703   0.0273
  -5.250  -0.2525   0.02979   0.02530  -0.0391   0.6695   0.0277
  -5.000  -0.2403   0.02840   0.02386  -0.0366   0.6686   0.0279
  -4.750  -0.2265   0.02724   0.02263  -0.0342   0.6675   0.0281
  -4.500  -0.2119   0.02618   0.02150  -0.0319   0.6664   0.0283
  -4.250  -0.1965   0.02515   0.02039  -0.0297   0.6652   0.0285
  -4.000  -0.1803   0.02419   0.01934  -0.0275   0.6642   0.0289
  -3.750  -0.1633   0.02319   0.01824  -0.0254   0.6631   0.0294
  -3.500  -0.1450   0.02227   0.01720  -0.0235   0.6621   0.0301
  -3.250  -0.1240   0.02233   0.01700  -0.0211   0.6611   0.0323
  -3.000  -0.1070   0.02172   0.01618  -0.0185   0.6602   0.0325
  -2.750  -0.0887   0.01825   0.01246  -0.0169   0.6593   0.0335
  -2.500  -0.0628   0.01755   0.01176  -0.0168   0.6582   0.0342
  -2.250  -0.0373   0.01690   0.01104  -0.0164   0.6570   0.0348
  -2.000  -0.0118   0.01643   0.01049  -0.0159   0.6555   0.0361
  -1.750   0.0424   0.01397   0.00770  -0.0211   0.6549   0.0309
  -1.500   0.1094   0.01225   0.00588  -0.0298   0.6544   0.0294
  -1.250   0.1476   0.01183   0.00547  -0.0323   0.6535   0.0301
  -1.000   0.1911   0.01120   0.00484  -0.0359   0.6526   0.0301
  -0.750   0.2274   0.01083   0.00447  -0.0380   0.6516   0.0305
  -0.500   0.2584   0.01061   0.00426  -0.0388   0.6505   0.0314
  -0.250   0.2896   0.01033   0.00398  -0.0397   0.6494   0.0315
   0.000   0.3189   0.01014   0.00379  -0.0401   0.6482   0.0320
   0.250   0.3471   0.01006   0.00372  -0.0403   0.6470   0.0325
   0.500   0.3774   0.00977   0.00342  -0.0410   0.6461   0.0329
   0.750   0.4073   0.00956   0.00321  -0.0416   0.6451   0.0337
   1.000   0.4366   0.00943   0.00310  -0.0420   0.6441   0.0353
   1.250   0.4658   0.00936   0.00303  -0.0425   0.6430   0.0365
   1.500   0.4950   0.00932   0.00300  -0.0429   0.6417   0.0381
   1.750   0.5239   0.00931   0.00300  -0.0434   0.6403   0.0396
   2.000   0.5531   0.00925   0.00299  -0.0439   0.6394   0.0442
   2.250   0.7515   0.00839   0.00463  -0.0829   0.6395   0.9195
   2.500   0.7409   0.00906   0.00533  -0.0745   0.6382   0.9699
   2.750   0.7776   0.00928   0.00555  -0.0766   0.6370   0.9741
   3.000   0.8181   0.00936   0.00565  -0.0797   0.6357   0.9777
   3.250   0.8734   0.00941   0.00571  -0.0859   0.6343   0.9859
   3.500   0.9120   0.00925   0.00555  -0.0884   0.6318   0.9893
   3.750   0.9500   0.00894   0.00522  -0.0908   0.6289   0.9913
   4.000   0.9829   0.00916   0.00542  -0.0922   0.6266   0.9951
   4.250   1.0188   0.00868   0.00498  -0.0942   0.6233   0.9963
   4.500   1.0544   0.00831   0.00465  -0.0962   0.6186   0.9980
   4.750   1.0873   0.00801   0.00428  -0.0974   0.6109   0.9993
   5.000   1.1164   0.00791   0.00425  -0.0980   0.6037   0.9998
   5.250   1.1435   0.00788   0.00419  -0.0981   0.5963   1.0000
   6.500   1.2195   0.01520   0.01031  -0.0952   0.3150   1.0000
   6.750   1.1908   0.01806   0.01301  -0.0882   0.2762   1.0000
   7.000   1.1626   0.02009   0.01496  -0.0803   0.2560   1.0000
  17.000   1.4295   0.08265   0.07746  -0.0269   0.0135   0.9999
  17.250   1.4357   0.08469   0.07956  -0.0265   0.0134   0.9999
  17.500   1.4434   0.08665   0.08160  -0.0264   0.0130   0.9999
  17.750   1.4468   0.08902   0.08404  -0.0260   0.0129   0.9999
  18.000   1.4520   0.09127   0.08636  -0.0257   0.0126   0.9999
  18.250   1.4553   0.09373   0.08889  -0.0256   0.0125   0.9999
  18.500   1.4600   0.09605   0.09127  -0.0255   0.0123   0.9998
  18.750   1.4617   0.09874   0.09404  -0.0253   0.0121   0.9998
  19.000   1.4654   0.10128   0.09662  -0.0255   0.0118   0.9998
  19.250   1.4667   0.10409   0.09950  -0.0255   0.0117   0.9998
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