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

SA7038 (sa7038-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 50,000
Max Cl/Cd: 34.64 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7038-il-50000.txt
Download as CSV file: xf-sa7038-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7038                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3549   0.10394   0.09729  -0.0243   1.0000   0.2129
  -8.000  -0.3471   0.10037   0.09378  -0.0234   1.0000   0.2206
  -7.750  -0.3643   0.09992   0.09350  -0.0234   1.0000   0.2287
  -7.500  -0.3524   0.09612   0.08973  -0.0218   1.0000   0.2412
  -7.250  -0.3481   0.09307   0.08677  -0.0202   1.0000   0.2517
  -7.000  -0.3783   0.09347   0.08740  -0.0185   1.0000   0.2579
  -6.750  -0.3714   0.09024   0.08422  -0.0163   1.0000   0.2714
  -6.500  -0.3653   0.08711   0.08114  -0.0141   1.0000   0.2830
  -6.250  -0.3703   0.08487   0.07901  -0.0117   1.0000   0.2936
  -6.000  -0.3818   0.08314   0.07742  -0.0099   1.0000   0.3050
  -5.500  -0.3901   0.07870   0.07317  -0.0051   1.0000   0.3342
  -5.250  -0.3912   0.07639   0.07094  -0.0024   1.0000   0.3498
  -5.000  -0.3916   0.07406   0.06869   0.0006   1.0000   0.3682
  -4.000  -0.3169   0.04670   0.03984  -0.0435   1.0000   0.1468
  -3.750  -0.2854   0.04134   0.03373  -0.0468   1.0000   0.1246
  -3.500  -0.2537   0.03721   0.02863  -0.0487   1.0000   0.1136
  -3.250  -0.2283   0.03441   0.02546  -0.0490   1.0000   0.1120
  -3.000  -0.2009   0.03221   0.02265  -0.0492   1.0000   0.1138
  -2.750  -0.1762   0.03018   0.02049  -0.0491   1.0000   0.1190
  -2.500  -0.1502   0.02854   0.01851  -0.0488   1.0000   0.1229
  -2.250  -0.1242   0.02704   0.01662  -0.0481   1.0000   0.1300
  -2.000  -0.1011   0.02585   0.01546  -0.0474   1.0000   0.1486
  -1.750  -0.0765   0.02463   0.01432  -0.0466   1.0000   0.1890
  -1.500  -0.0463   0.02135   0.01314  -0.0464   1.0000   0.4999
  -1.250  -0.0377   0.01969   0.01253  -0.0408   1.0000   1.0000
  -1.000  -0.0154   0.02010   0.01231  -0.0408   1.0000   1.0000
  -0.750   0.0055   0.02056   0.01233  -0.0407   1.0000   1.0000
  -0.500   0.0258   0.02107   0.01249  -0.0406   1.0000   1.0000
  -0.250   0.0455   0.02164   0.01276  -0.0406   1.0000   1.0000
   0.000   0.0646   0.02227   0.01310  -0.0405   1.0000   1.0000
   0.250   0.0833   0.02295   0.01356  -0.0405   1.0000   1.0000
   0.500   0.1090   0.02385   0.01424  -0.0419   0.9965   1.0000
   0.750   0.1621   0.02526   0.01538  -0.0481   0.9794   1.0000
   1.000   0.2117   0.02650   0.01640  -0.0535   0.9616   1.0000
   1.250   0.2619   0.02767   0.01740  -0.0588   0.9441   1.0000
   1.500   0.3051   0.02861   0.01822  -0.0626   0.9255   1.0000
   1.750   0.3464   0.02944   0.01897  -0.0658   0.9064   1.0000
   2.000   0.3916   0.03020   0.01967  -0.0694   0.8883   1.0000
   2.250   0.4345   0.03085   0.02028  -0.0724   0.8700   1.0000
   2.500   0.4691   0.03142   0.02086  -0.0740   0.8502   1.0000
   2.750   0.5125   0.03182   0.02128  -0.0765   0.8320   1.0000
   3.000   0.5618   0.03195   0.02146  -0.0795   0.8148   1.0000
   3.250   0.5893   0.03241   0.02196  -0.0795   0.7937   1.0000
   3.500   0.6353   0.03228   0.02192  -0.0814   0.7756   1.0000
   3.750   0.6834   0.03179   0.02157  -0.0830   0.7588   1.0000
   4.000   0.7130   0.03192   0.02178  -0.0825   0.7381   1.0000
   4.250   0.7526   0.03146   0.02143  -0.0826   0.7195   1.0000
   4.500   0.7975   0.03057   0.02070  -0.0828   0.7019   1.0000
   4.750   0.8246   0.03064   0.02087  -0.0815   0.6796   1.0000
   5.000   0.8647   0.02985   0.02017  -0.0809   0.6598   1.0000
   5.250   0.8922   0.02987   0.02033  -0.0794   0.6365   1.0000
   5.500   0.9298   0.02921   0.01970  -0.0785   0.6147   1.0000
   5.750   0.9547   0.02945   0.02002  -0.0768   0.5894   1.0000
   6.000   0.9804   0.02970   0.02032  -0.0752   0.5641   1.0000
   6.250   1.0075   0.02991   0.02060  -0.0737   0.5390   1.0000
   6.500   1.0354   0.03009   0.02076  -0.0722   0.5135   1.0000
   6.750   1.0595   0.03059   0.02129  -0.0706   0.4874   1.0000
   7.000   1.0809   0.03134   0.02210  -0.0689   0.4610   1.0000
   7.250   1.1025   0.03211   0.02295  -0.0672   0.4348   1.0000
   7.500   1.1248   0.03295   0.02380  -0.0656   0.4096   1.0000
   7.750   1.1482   0.03373   0.02454  -0.0641   0.3843   1.0000
   8.000   1.1683   0.03479   0.02565  -0.0624   0.3593   1.0000
   8.250   1.1856   0.03613   0.02711  -0.0606   0.3352   1.0000
   8.500   1.2055   0.03730   0.02832  -0.0589   0.3112   1.0000
   8.750   1.2263   0.03845   0.02940  -0.0574   0.2872   1.0000
   9.000   1.2384   0.04017   0.03133  -0.0551   0.2650   1.0000
   9.250   1.2580   0.04158   0.03265  -0.0536   0.2427   1.0000
   9.500   1.2680   0.04366   0.03498  -0.0513   0.2232   1.0000
   9.750   1.2875   0.04538   0.03659  -0.0499   0.2031   1.0000
  10.000   1.2967   0.04778   0.03916  -0.0477   0.1867   1.0000
  10.250   1.3065   0.05060   0.04224  -0.0456   0.1730   1.0000
  10.500   1.3147   0.05316   0.04495  -0.0435   0.1597   1.0000
  10.750   1.3104   0.05662   0.04886  -0.0406   0.1515   1.0000
  11.000   1.3097   0.06046   0.05295  -0.0384   0.1447   1.0000
  11.250   1.2910   0.06474   0.05767  -0.0353   0.1417   1.0000
  11.500   1.2968   0.06752   0.06047  -0.0336   0.1321   1.0000
  11.750   1.2706   0.07186   0.06511  -0.0307   0.1317   1.0000
  12.000   1.2428   0.07673   0.07022  -0.0289   0.1320   1.0000
  12.250   1.2152   0.08240   0.07606  -0.0287   0.1327   1.0000
  12.500   1.1877   0.08889   0.08268  -0.0299   0.1336   1.0000
  12.750   0.9578   0.14088   0.13390  -0.0690   0.2039   1.0000
  13.000   0.9653   0.14650   0.13961  -0.0698   0.2023   1.0000
<< Back to SA7038 (sa7038-il)

Polar data table (+)

Polar graphs


<< Back to SA7038 (sa7038-il)