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

SA7035 (sa7035-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 50,000
Max Cl/Cd: 33.24 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7035-il-50000.txt
Download as CSV file: xf-sa7035-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7035                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3847   0.09517   0.08866  -0.0157   1.0000   0.2608
  -7.500  -0.3852   0.09254   0.08613  -0.0153   1.0000   0.2729
  -7.250  -0.4081   0.09220   0.08597  -0.0151   1.0000   0.2829
  -7.000  -0.3920   0.08777   0.08158  -0.0133   1.0000   0.2993
  -6.750  -0.4113   0.08701   0.08100  -0.0119   1.0000   0.3116
  -6.000  -0.3919   0.07736   0.07157  -0.0052   1.0000   0.3586
  -5.750  -0.3906   0.07473   0.06904  -0.0028   1.0000   0.3756
  -5.500  -0.4077   0.07352   0.06799  -0.0002   1.0000   0.3982
  -5.000  -0.4006   0.05091   0.04410  -0.0402   1.0000   0.1421
  -4.750  -0.3823   0.04591   0.03872  -0.0407   1.0000   0.1233
  -4.500  -0.3617   0.04122   0.03331  -0.0415   1.0000   0.1110
  -4.250  -0.3416   0.03763   0.02934  -0.0412   1.0000   0.1064
  -4.000  -0.3179   0.03418   0.02520  -0.0410   1.0000   0.1026
  -3.750  -0.2950   0.03170   0.02234  -0.0403   1.0000   0.1046
  -3.500  -0.2710   0.02967   0.01984  -0.0396   1.0000   0.1104
  -3.250  -0.2465   0.02755   0.01742  -0.0387   1.0000   0.1169
  -3.000  -0.2218   0.02589   0.01548  -0.0377   1.0000   0.1280
  -2.750  -0.1978   0.02429   0.01394  -0.0366   1.0000   0.1532
  -2.500  -0.1734   0.02247   0.01243  -0.0356   1.0000   0.2155
  -2.250  -0.1567   0.01886   0.01143  -0.0321   1.0000   0.5922
  -2.000  -0.1280   0.01772   0.01086  -0.0284   1.0000   1.0000
  -1.750  -0.1074   0.01783   0.01037  -0.0284   1.0000   1.0000
  -1.500  -0.0871   0.01802   0.01010  -0.0281   1.0000   1.0000
  -1.250  -0.0671   0.01827   0.00994  -0.0278   1.0000   1.0000
  -1.000  -0.0473   0.01858   0.00991  -0.0275   1.0000   1.0000
  -0.750  -0.0279   0.01894   0.00998  -0.0272   1.0000   1.0000
  -0.500  -0.0087   0.01936   0.01014  -0.0269   1.0000   1.0000
  -0.250   0.0102   0.01982   0.01038  -0.0266   1.0000   1.0000
   0.000   0.0286   0.02035   0.01068  -0.0264   1.0000   1.0000
   0.250   0.0468   0.02093   0.01109  -0.0263   1.0000   1.0000
   0.500   0.0646   0.02158   0.01159  -0.0262   1.0000   1.0000
   0.750   0.0916   0.02246   0.01232  -0.0280   0.9957   1.0000
   1.000   0.1468   0.02380   0.01348  -0.0348   0.9769   1.0000
   1.250   0.2019   0.02504   0.01459  -0.0412   0.9581   1.0000
   1.500   0.2492   0.02602   0.01548  -0.0460   0.9381   1.0000
   1.750   0.2976   0.02690   0.01632  -0.0506   0.9180   1.0000
   2.000   0.3456   0.02765   0.01705  -0.0549   0.8985   1.0000
   2.250   0.3862   0.02825   0.01767  -0.0577   0.8773   1.0000
   2.500   0.4383   0.02866   0.01814  -0.0619   0.8584   1.0000
   2.750   0.4729   0.02910   0.01863  -0.0632   0.8365   1.0000
   3.000   0.5251   0.02914   0.01880  -0.0666   0.8174   1.0000
   3.250   0.5621   0.02932   0.01906  -0.0676   0.7962   1.0000
   3.500   0.6059   0.02911   0.01897  -0.0690   0.7766   1.0000
   3.750   0.6452   0.02889   0.01891  -0.0694   0.7564   1.0000
   4.000   0.6808   0.02868   0.01882  -0.0692   0.7352   1.0000
   4.250   0.7177   0.02830   0.01856  -0.0687   0.7144   1.0000
   4.500   0.7506   0.02802   0.01839  -0.0677   0.6919   1.0000
   4.750   0.7801   0.02791   0.01843  -0.0663   0.6681   1.0000
   5.000   0.8138   0.02749   0.01808  -0.0649   0.6451   1.0000
   5.250   0.8416   0.02748   0.01815  -0.0632   0.6196   1.0000
   5.500   0.8670   0.02769   0.01847  -0.0615   0.5931   1.0000
   5.750   0.8923   0.02795   0.01879  -0.0597   0.5661   1.0000
   6.000   0.9172   0.02827   0.01915  -0.0579   0.5386   1.0000
   6.250   0.9416   0.02866   0.01958  -0.0562   0.5104   1.0000
   6.500   0.9653   0.02915   0.02014  -0.0544   0.4818   1.0000
   6.750   0.9883   0.02975   0.02075  -0.0526   0.4528   1.0000
   7.000   1.0108   0.03041   0.02142  -0.0508   0.4235   1.0000
   7.250   1.0328   0.03119   0.02219  -0.0491   0.3942   1.0000
   7.500   1.0545   0.03204   0.02300  -0.0473   0.3647   1.0000
   7.750   1.0745   0.03298   0.02396  -0.0455   0.3344   1.0000
   8.000   1.0918   0.03415   0.02519  -0.0434   0.3042   1.0000
   8.250   1.1085   0.03544   0.02649  -0.0414   0.2744   1.0000
   8.500   1.1248   0.03694   0.02800  -0.0394   0.2458   1.0000
   8.750   1.1400   0.03856   0.02960  -0.0374   0.2182   1.0000
   9.000   1.1570   0.04065   0.03163  -0.0356   0.1940   1.0000
   9.250   1.1684   0.04275   0.03388  -0.0335   0.1723   1.0000
   9.500   1.1852   0.04548   0.03655  -0.0320   0.1544   1.0000
   9.750   1.1929   0.04824   0.03964  -0.0298   0.1398   1.0000
  10.000   1.2051   0.05154   0.04305  -0.0282   0.1278   1.0000
  10.250   1.1968   0.05543   0.04763  -0.0251   0.1221   1.0000
  10.500   1.2033   0.05864   0.05092  -0.0234   0.1130   1.0000
  10.750   1.1887   0.06314   0.05592  -0.0208   0.1111   1.0000
  11.000   1.1706   0.06769   0.06084  -0.0186   0.1104   1.0000
  11.250   1.1469   0.07211   0.06551  -0.0165   0.1107   1.0000
  11.500   1.1212   0.07706   0.07065  -0.0157   0.1116   1.0000
  11.750   1.0950   0.08278   0.07651  -0.0166   0.1127   1.0000
  12.000   1.0703   0.08930   0.08312  -0.0188   0.1139   1.0000
  12.250   1.0479   0.09662   0.09049  -0.0220   0.1148   1.0000
<< Back to SA7035 (sa7035-il)

Polar data table (+)

Polar graphs


<< Back to SA7035 (sa7035-il)