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SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD7037-092-88 (sd7037-il)
Reynolds number: 200,000
Max Cl/Cd: 70.76 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7037-il-200000-n5.txt
Download as CSV file: xf-sd7037-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7037-092-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3007   0.08106   0.07770  -0.0353   1.0000   0.0191
  -8.750  -0.3030   0.07738   0.07406  -0.0356   1.0000   0.0185
  -8.500  -0.3772   0.08694   0.08341  -0.0341   1.0000   0.0230
  -8.250  -0.3856   0.08211   0.07864  -0.0351   1.0000   0.0180
  -7.750  -0.4310   0.07222   0.06894  -0.0360   1.0000   0.0154
  -7.500  -0.4412   0.06920   0.06598  -0.0363   1.0000   0.0153
  -7.250  -0.4350   0.06382   0.06058  -0.0423   0.9969   0.0151
  -7.000  -0.4144   0.05418   0.05075  -0.0543   0.9897   0.0150
  -6.750  -0.3930   0.04407   0.04024  -0.0640   0.9836   0.0150
  -6.500  -0.3731   0.03563   0.03109  -0.0695   0.9765   0.0153
  -6.250  -0.3447   0.03084   0.02574  -0.0730   0.9729   0.0152
  -6.000  -0.3204   0.02725   0.02162  -0.0742   0.9671   0.0151
  -5.750  -0.2904   0.02427   0.01811  -0.0758   0.9631   0.0151
  -5.500  -0.2571   0.02188   0.01525  -0.0776   0.9603   0.0152
  -5.250  -0.2275   0.02016   0.01315  -0.0782   0.9558   0.0154
  -5.000  -0.1979   0.01875   0.01147  -0.0786   0.9507   0.0156
  -4.750  -0.1658   0.01740   0.01000  -0.0797   0.9470   0.0161
  -4.500  -0.1347   0.01642   0.00895  -0.0805   0.9428   0.0168
  -4.250  -0.1070   0.01574   0.00819  -0.0805   0.9361   0.0181
  -4.000  -0.0750   0.01508   0.00741  -0.0812   0.9316   0.0199
  -3.750  -0.0476   0.01435   0.00664  -0.0811   0.9249   0.0209
  -3.500  -0.0184   0.01377   0.00601  -0.0813   0.9184   0.0224
  -3.250   0.0111   0.01329   0.00542  -0.0815   0.9124   0.0247
  -3.000   0.0384   0.01282   0.00492  -0.0812   0.9043   0.0291
  -2.750   0.0671   0.01227   0.00446  -0.0812   0.8974   0.0504
  -2.500   0.0939   0.01178   0.00413  -0.0810   0.8885   0.0960
  -2.250   0.1207   0.01125   0.00390  -0.0809   0.8798   0.1720
  -2.000   0.1476   0.01063   0.00370  -0.0809   0.8710   0.2866
  -1.750   0.1733   0.01021   0.00354  -0.0805   0.8600   0.3765
  -1.500   0.1991   0.00977   0.00342  -0.0799   0.8493   0.4795
  -1.250   0.2240   0.00933   0.00333  -0.0790   0.8383   0.5951
  -1.000   0.2479   0.00900   0.00326  -0.0776   0.8260   0.6914
  -0.750   0.2709   0.00877   0.00319  -0.0760   0.8124   0.7716
  -0.500   0.2944   0.00858   0.00310  -0.0742   0.7982   0.8449
  -0.250   0.3246   0.00844   0.00297  -0.0739   0.7830   0.9159
   0.000   0.3679   0.00835   0.00275  -0.0768   0.7666   0.9832
   0.250   0.3978   0.00838   0.00264  -0.0771   0.7483   1.0000
   0.500   0.4239   0.00846   0.00257  -0.0766   0.7293   1.0000
   0.750   0.4500   0.00856   0.00252  -0.0760   0.7100   1.0000
   1.000   0.4761   0.00869   0.00250  -0.0755   0.6905   1.0000
   1.250   0.5021   0.00882   0.00250  -0.0750   0.6702   1.0000
   1.500   0.5281   0.00898   0.00252  -0.0745   0.6497   1.0000
   1.750   0.5539   0.00915   0.00256  -0.0740   0.6292   1.0000
   2.000   0.5798   0.00933   0.00262  -0.0735   0.6083   1.0000
   2.250   0.6054   0.00953   0.00271  -0.0730   0.5875   1.0000
   2.500   0.6311   0.00973   0.00281  -0.0725   0.5665   1.0000
   2.750   0.6567   0.00994   0.00292  -0.0720   0.5452   1.0000
   3.000   0.6821   0.01017   0.00304  -0.0715   0.5244   1.0000
   3.250   0.7076   0.01041   0.00320  -0.0711   0.5030   1.0000
   3.750   0.7580   0.01093   0.00355  -0.0701   0.4606   1.0000
   4.000   0.7830   0.01121   0.00376  -0.0696   0.4392   1.0000
   4.250   0.8079   0.01150   0.00398  -0.0690   0.4181   1.0000
   4.500   0.8327   0.01180   0.00421  -0.0685   0.3968   1.0000
   4.750   0.8572   0.01213   0.00447  -0.0680   0.3759   1.0000
   5.000   0.8817   0.01246   0.00476  -0.0675   0.3548   1.0000
   5.250   0.9058   0.01283   0.00506  -0.0669   0.3341   1.0000
   5.500   0.9300   0.01319   0.00538  -0.0663   0.3139   1.0000
   5.750   0.9539   0.01358   0.00574  -0.0657   0.2935   1.0000
   6.250   1.0010   0.01442   0.00650  -0.0645   0.2555   1.0000
   6.500   1.0243   0.01487   0.00692  -0.0639   0.2372   1.0000
   6.750   1.0471   0.01535   0.00738  -0.0632   0.2188   1.0000
   7.000   1.0695   0.01586   0.00785  -0.0624   0.2012   1.0000
   7.250   1.0919   0.01637   0.00835  -0.0617   0.1837   1.0000
   7.500   1.1140   0.01690   0.00887  -0.0610   0.1677   1.0000
   7.750   1.1356   0.01746   0.00945  -0.0601   0.1526   1.0000
   8.000   1.1564   0.01808   0.01003  -0.0593   0.1357   1.0000
   8.250   1.1764   0.01877   0.01066  -0.0583   0.1185   1.0000
   8.500   1.1963   0.01945   0.01132  -0.0573   0.1011   1.0000
   8.750   1.2155   0.02018   0.01204  -0.0563   0.0863   1.0000
   9.000   1.2339   0.02096   0.01280  -0.0551   0.0728   1.0000
   9.250   1.2512   0.02181   0.01362  -0.0539   0.0600   1.0000
   9.500   1.2675   0.02271   0.01451  -0.0525   0.0487   1.0000
   9.750   1.2823   0.02370   0.01549  -0.0509   0.0374   1.0000
  10.000   1.2954   0.02478   0.01660  -0.0491   0.0286   1.0000
  10.250   1.3054   0.02592   0.01778  -0.0468   0.0228   1.0000
  10.500   1.3141   0.02711   0.01904  -0.0444   0.0193   1.0000
  10.750   1.3221   0.02835   0.02039  -0.0421   0.0173   1.0000
  11.000   1.3292   0.02966   0.02182  -0.0398   0.0159   1.0000
  11.250   1.3341   0.03117   0.02343  -0.0376   0.0150   1.0000
  11.500   1.3378   0.03280   0.02519  -0.0355   0.0143   1.0000
  11.750   1.3416   0.03449   0.02706  -0.0336   0.0137   1.0000
  12.000   1.3444   0.03635   0.02907  -0.0319   0.0130   1.0000
  12.250   1.3458   0.03841   0.03127  -0.0305   0.0125   1.0000
  12.500   1.3463   0.04068   0.03368  -0.0293   0.0120   1.0000
  12.750   1.3446   0.04331   0.03644  -0.0285   0.0117   1.0000
  13.000   1.3406   0.04636   0.03964  -0.0280   0.0115   1.0000
  13.250   1.3338   0.04994   0.04335  -0.0280   0.0112   1.0000
  13.500   1.3294   0.05348   0.04704  -0.0283   0.0111   1.0000
  13.750   1.3240   0.05735   0.05108  -0.0290   0.0109   1.0000
  14.000   1.3186   0.06140   0.05530  -0.0300   0.0108   1.0000
  14.250   1.3116   0.06585   0.05992  -0.0314   0.0107   1.0000
  14.500   1.3040   0.07064   0.06488  -0.0330   0.0106   1.0000
  14.750   1.2961   0.07560   0.07000  -0.0349   0.0105   1.0000
  15.000   1.2878   0.08086   0.07542  -0.0371   0.0104   1.0000
  15.250   1.2790   0.08636   0.08108  -0.0395   0.0104   1.0000
  15.500   1.2697   0.09211   0.08702  -0.0422   0.0103   1.0000
  15.750   1.2602   0.09809   0.09315  -0.0451   0.0102   1.0000
  16.000   1.2507   0.10423   0.09945  -0.0482   0.0102   1.0000
  16.250   1.2412   0.11053   0.10590  -0.0514   0.0101   1.0000
  16.500   1.2311   0.11712   0.11264  -0.0549   0.0101   1.0000
  16.750   1.2210   0.12391   0.11958  -0.0587   0.0100   1.0000
  17.000   1.2103   0.13103   0.12685  -0.0627   0.0100   1.0000
  17.250   1.1996   0.13829   0.13427  -0.0670   0.0100   1.0000
  17.500   1.1883   0.14593   0.14206  -0.0715   0.0100   1.0000
  17.750   1.1765   0.15402   0.15029  -0.0765   0.0100   1.0000
  18.000   1.1635   0.16275   0.15917  -0.0819   0.0101   1.0000
  18.250   1.1479   0.17262   0.16917  -0.0881   0.0101   1.0000
  18.500   1.1256   0.18532   0.18202  -0.0959   0.0103   1.0000
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