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SA7026 (sa7026-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 50,000
Max Cl/Cd: 38.44 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7026-il-50000.txt
Download as CSV file: xf-sa7026-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 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  -0.3674   0.10508   0.09894  -0.0276   1.0000   0.2007
  -7.500  -0.3507   0.10028   0.09415  -0.0255   1.0000   0.2092
  -7.250  -0.3740   0.10035   0.09438  -0.0230   1.0000   0.2140
  -7.000  -0.3731   0.09732   0.09143  -0.0208   1.0000   0.2196
  -6.750  -0.3874   0.09630   0.09052  -0.0178   1.0000   0.2269
  -6.500  -0.4198   0.09695   0.09135  -0.0181   1.0000   0.2297
  -6.250  -0.4061   0.09269   0.08711  -0.0140   1.0000   0.2416
  -6.000  -0.4074   0.08996   0.08445  -0.0117   1.0000   0.2494
  -5.750  -0.4277   0.08917   0.08379  -0.0131   1.0000   0.2586
  -5.500  -0.4264   0.08648   0.08115  -0.0105   1.0000   0.2715
  -5.250  -0.4237   0.08353   0.07825  -0.0076   1.0000   0.2839
  -5.000  -0.4255   0.08107   0.07586  -0.0062   1.0000   0.2982
  -4.750  -0.4305   0.07890   0.07375  -0.0066   1.0000   0.3158
  -4.500  -0.4264   0.07588   0.07079  -0.0029   1.0000   0.3324
  -4.250  -0.4234   0.07340   0.06835   0.0000   1.0000   0.3519
  -4.000  -0.4226   0.07090   0.06587   0.0022   1.0000   0.3768
  -3.250  -0.2599   0.04477   0.03734  -0.0515   1.0000   0.1289
  -3.000  -0.2256   0.04060   0.03242  -0.0540   1.0000   0.1153
  -2.750  -0.1981   0.03775   0.02918  -0.0549   1.0000   0.1134
  -2.500  -0.1697   0.03529   0.02621  -0.0556   1.0000   0.1119
  -2.250  -0.1415   0.03314   0.02357  -0.0559   1.0000   0.1107
  -2.000  -0.1139   0.03135   0.02130  -0.0557   1.0000   0.1113
  -1.750  -0.0875   0.02999   0.01952  -0.0553   1.0000   0.1145
  -1.500  -0.0632   0.02880   0.01820  -0.0547   1.0000   0.1237
  -1.250  -0.0384   0.02791   0.01713  -0.0540   1.0000   0.1454
  -1.000  -0.0076   0.02639   0.01609  -0.0544   1.0000   0.2370
  -0.750   0.0136   0.02280   0.01498  -0.0512   1.0000   1.0000
  -0.500   0.0355   0.02332   0.01492  -0.0510   1.0000   1.0000
  -0.250   0.0566   0.02388   0.01503  -0.0508   1.0000   1.0000
   0.000   0.0770   0.02449   0.01525  -0.0506   1.0000   1.0000
   0.250   0.0969   0.02513   0.01559  -0.0505   1.0000   1.0000
   0.500   0.1165   0.02583   0.01603  -0.0503   1.0000   1.0000
   0.750   0.1356   0.02658   0.01654  -0.0502   1.0000   1.0000
   1.000   0.1543   0.02737   0.01714  -0.0501   1.0000   1.0000
   1.250   0.1805   0.02843   0.01798  -0.0516   0.9963   1.0000
   1.500   0.2288   0.03008   0.01940  -0.0570   0.9814   1.0000
   1.750   0.2711   0.03148   0.02062  -0.0613   0.9658   1.0000
   2.000   0.3116   0.03279   0.02181  -0.0650   0.9500   1.0000
   2.250   0.3516   0.03406   0.02298  -0.0685   0.9340   1.0000
   2.500   0.3922   0.03528   0.02414  -0.0719   0.9178   1.0000
   2.750   0.4339   0.03645   0.02527  -0.0753   0.9019   1.0000
   3.000   0.4633   0.03738   0.02620  -0.0766   0.8845   1.0000
   3.250   0.4959   0.03832   0.02715  -0.0783   0.8673   1.0000
   3.500   0.5314   0.03923   0.02811  -0.0802   0.8505   1.0000
   3.750   0.5702   0.04004   0.02898  -0.0825   0.8341   1.0000
   4.000   0.6041   0.04079   0.02980  -0.0838   0.8171   1.0000
   4.250   0.6305   0.04157   0.03066  -0.0841   0.7986   1.0000
   4.500   0.6663   0.04210   0.03135  -0.0854   0.7810   1.0000
   4.750   0.7083   0.04235   0.03175  -0.0870   0.7643   1.0000
   5.000   0.7327   0.04299   0.03251  -0.0866   0.7449   1.0000
   5.250   0.7672   0.04318   0.03288  -0.0870   0.7265   1.0000
   5.500   0.8123   0.04274   0.03272  -0.0881   0.7095   1.0000
   5.750   0.8407   0.04291   0.03309  -0.0874   0.6897   1.0000
   6.000   0.8805   0.04225   0.03268  -0.0873   0.6709   1.0000
   6.250   0.9420   0.03984   0.03072  -0.0883   0.6541   1.0000
   6.500   0.9781   0.03888   0.03003  -0.0871   0.6324   1.0000
   6.750   1.0508   0.03497   0.02660  -0.0878   0.6110   1.0000
   7.000   1.0973   0.03301   0.02490  -0.0868   0.5824   1.0000
   7.250   1.1261   0.03241   0.02449  -0.0846   0.5494   1.0000
   7.500   1.1636   0.03126   0.02340  -0.0829   0.5111   1.0000
   7.750   1.1882   0.03104   0.02322  -0.0802   0.4689   1.0000
   8.000   1.2054   0.03136   0.02349  -0.0769   0.4242   1.0000
   8.250   1.2192   0.03199   0.02397  -0.0735   0.3769   1.0000
   8.500   1.2280   0.03299   0.02474  -0.0696   0.3276   1.0000
   8.750   1.2311   0.03439   0.02584  -0.0654   0.2776   1.0000
   9.000   1.2291   0.03624   0.02739  -0.0609   0.2292   1.0000
   9.250   1.2261   0.03852   0.02933  -0.0566   0.1846   1.0000
   9.500   1.2238   0.04114   0.03163  -0.0527   0.1470   1.0000
   9.750   1.2228   0.04373   0.03405  -0.0492   0.1190   1.0000
  10.000   1.2351   0.04701   0.03717  -0.0474   0.0968   1.0000
  10.250   1.2623   0.05133   0.04169  -0.0470   0.0840   1.0000
  10.500   1.2807   0.05497   0.04559  -0.0460   0.0767   1.0000
  10.750   1.2877   0.05910   0.05011  -0.0441   0.0731   1.0000
  11.000   1.2829   0.06268   0.05419  -0.0409   0.0712   1.0000
  11.250   1.2753   0.06639   0.05829  -0.0380   0.0702   1.0000
  11.500   1.2632   0.07030   0.06256  -0.0353   0.0698   1.0000
  11.750   1.2471   0.07443   0.06702  -0.0331   0.0699   1.0000
  12.000   1.2276   0.07889   0.07177  -0.0315   0.0702   1.0000
  12.250   1.2060   0.08378   0.07693  -0.0309   0.0707   1.0000
  12.500   1.1832   0.08918   0.08255  -0.0313   0.0714   1.0000
  12.750   1.1601   0.09514   0.08870  -0.0328   0.0722   1.0000
  13.000   1.1377   0.10169   0.09539  -0.0352   0.0731   1.0000
  13.250   1.1179   0.10867   0.10248  -0.0382   0.0739   1.0000
  13.500   1.1010   0.11603   0.10991  -0.0416   0.0746   1.0000
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