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

S1091 (s1091-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S1091 (s1091-il)
Reynolds number: 200,000
Max Cl/Cd: 96.18 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1091-il-200000.txt
Download as CSV file: xf-s1091-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1091                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2922   0.09946   0.09613  -0.0164   1.0000   0.0187
  -6.750  -0.2997   0.09878   0.09552  -0.0146   1.0000   0.0190
  -6.500  -0.3023   0.09782   0.09464  -0.0148   1.0000   0.0192
  -6.250  -0.3020   0.09639   0.09327  -0.0153   1.0000   0.0193
  -6.000  -0.2991   0.09552   0.09245  -0.0181   1.0000   0.0195
  -5.750  -0.3007   0.09181   0.08883  -0.0166   1.0000   0.0198
  -5.500  -0.3027   0.08860   0.08566  -0.0128   1.0000   0.0202
  -5.250  -0.2979   0.08585   0.08293  -0.0119   0.9991   0.0209
  -5.000  -0.2656   0.08171   0.07877  -0.0185   0.9948   0.0226
  -4.750  -0.2302   0.07758   0.07463  -0.0263   0.9889   0.0239
  -4.500  -0.1855   0.07334   0.07034  -0.0365   0.9845   0.0258
  -4.250  -0.1178   0.06995   0.06683  -0.0537   0.9766   0.0273
  -4.000  -0.0697   0.06468   0.06150  -0.0640   0.9729   0.0278
  -3.750  -0.0581   0.06026   0.05711  -0.0631   0.9660   0.0289
  -3.500  -0.0233   0.05667   0.05350  -0.0680   0.9614   0.0308
  -3.250   0.0198   0.05305   0.04982  -0.0751   0.9561   0.0334
  -3.000   0.0999   0.04960   0.04612  -0.0908   0.9506   0.0380
  -2.750   0.1354   0.04415   0.04066  -0.0961   0.9472   0.0396
  -2.500   0.1642   0.04149   0.03798  -0.0981   0.9395   0.0427
  -2.250   0.2446   0.03830   0.03432  -0.1108   0.9360   0.0507
  -2.000   0.2727   0.03385   0.03003  -0.1136   0.9330   0.0545
  -1.750   0.3260   0.03040   0.02619  -0.1200   0.9252   0.0653
  -1.500   0.3638   0.02804   0.02387  -0.1229   0.9212   0.0743
  -0.750   0.5122   0.01632   0.01036  -0.1341   0.9071   0.0419
  -0.500   0.5508   0.01505   0.00863  -0.1350   0.8982   0.0382
  -0.250   0.5926   0.01319   0.00655  -0.1374   0.8920   0.0428
   0.000   0.6281   0.01224   0.00550  -0.1382   0.8806   0.0463
   0.250   0.6638   0.01147   0.00469  -0.1392   0.8688   0.0557
   0.500   0.6981   0.01064   0.00420  -0.1400   0.8561   0.1747
   0.750   0.7294   0.01027   0.00419  -0.1406   0.8421   0.3368
   1.000   0.7631   0.00906   0.00405  -0.1414   0.8283   1.0000
   1.250   0.7920   0.00916   0.00392  -0.1412   0.8130   1.0000
   1.500   0.8197   0.00929   0.00386  -0.1407   0.7973   1.0000
   1.750   0.8466   0.00944   0.00383  -0.1400   0.7812   1.0000
   2.000   0.8729   0.00960   0.00384  -0.1393   0.7648   1.0000
   2.250   0.8989   0.00977   0.00386  -0.1385   0.7481   1.0000
   2.500   0.9236   0.00993   0.00392  -0.1375   0.7297   1.0000
   2.750   0.9482   0.01010   0.00401  -0.1364   0.7106   1.0000
   3.000   0.9728   0.01029   0.00407  -0.1353   0.6914   1.0000
   3.250   0.9967   0.01047   0.00416  -0.1342   0.6701   1.0000
   3.500   1.0204   0.01067   0.00425  -0.1330   0.6478   1.0000
   3.750   1.0436   0.01086   0.00437  -0.1317   0.6234   1.0000
   4.000   1.0666   0.01109   0.00453  -0.1304   0.5971   1.0000
   4.250   1.0889   0.01133   0.00466  -0.1290   0.5667   1.0000
   4.500   1.1103   0.01163   0.00481  -0.1275   0.5304   1.0000
   4.750   1.1311   0.01200   0.00500  -0.1259   0.4894   1.0000
   5.000   1.1513   0.01248   0.00527  -0.1242   0.4483   1.0000
   5.250   1.1715   0.01301   0.00566  -0.1227   0.4105   1.0000
   5.500   1.1914   0.01360   0.00605  -0.1212   0.3735   1.0000
   5.750   1.2113   0.01419   0.00648  -0.1197   0.3356   1.0000
   6.000   1.2306   0.01485   0.00696  -0.1182   0.2968   1.0000
   6.250   1.2494   0.01559   0.00752  -0.1166   0.2565   1.0000
   6.500   1.2676   0.01640   0.00812  -0.1150   0.2168   1.0000
   6.750   1.2853   0.01730   0.00883  -0.1134   0.1829   1.0000
   7.000   1.3023   0.01829   0.00964  -0.1116   0.1580   1.0000
   7.250   1.3203   0.01921   0.01049  -0.1100   0.1402   1.0000
   7.500   1.3378   0.02018   0.01143  -0.1082   0.1280   1.0000
   7.750   1.3543   0.02128   0.01243  -0.1064   0.1186   1.0000
   8.000   1.3741   0.02199   0.01326  -0.1051   0.1112   1.0000
   8.250   1.3906   0.02324   0.01441  -0.1034   0.1053   1.0000
   8.500   1.4106   0.02404   0.01537  -0.1020   0.1010   1.0000
   8.750   1.4297   0.02498   0.01640  -0.1006   0.0970   1.0000
   9.000   1.4489   0.02632   0.01770  -0.0994   0.0935   1.0000
   9.250   1.4701   0.02766   0.01915  -0.0985   0.0909   1.0000
   9.500   1.4906   0.02873   0.02041  -0.0973   0.0885   1.0000
   9.750   1.5102   0.02980   0.02165  -0.0961   0.0855   1.0000
  10.000   1.5299   0.03095   0.02287  -0.0951   0.0828   1.0000
  10.250   1.5540   0.03313   0.02510  -0.0950   0.0801   1.0000
  10.500   1.5729   0.03471   0.02695  -0.0937   0.0783   1.0000
  10.750   1.5885   0.03588   0.02839  -0.0920   0.0760   1.0000
  11.000   1.6033   0.03709   0.02982  -0.0902   0.0733   1.0000
  11.250   1.6178   0.03824   0.03111  -0.0885   0.0705   1.0000
  11.500   1.6341   0.04087   0.03382  -0.0878   0.0669   1.0000
  11.750   1.6360   0.04111   0.03438  -0.0841   0.0642   1.0000
  12.000   1.6349   0.04126   0.03466  -0.0800   0.0607   1.0000
  12.250   1.6343   0.04137   0.03466  -0.0766   0.0568   1.0000
  12.500   1.6309   0.04260   0.03610  -0.0732   0.0537   1.0000
  12.750   1.6268   0.04336   0.03709  -0.0699   0.0505   1.0000
  13.000   1.6267   0.04433   0.03817  -0.0677   0.0476   1.0000
  13.250   1.6258   0.04630   0.04013  -0.0659   0.0444   1.0000
  13.500   1.6247   0.04773   0.04195  -0.0644   0.0412   1.0000
  13.750   1.6240   0.04914   0.04342  -0.0639   0.0347   1.0000
  14.000   1.6225   0.05203   0.04629  -0.0638   0.0166   1.0000
  14.250   1.6071   0.05689   0.05124  -0.0636   0.0141   1.0000
  14.500   1.5931   0.06190   0.05645  -0.0639   0.0129   1.0000
  14.750   1.5801   0.06707   0.06187  -0.0647   0.0118   1.0000
  15.000   1.5653   0.07279   0.06780  -0.0662   0.0111   1.0000
  15.250   1.5484   0.07926   0.07445  -0.0685   0.0106   1.0000
  15.500   1.5309   0.08622   0.08162  -0.0714   0.0105   1.0000
  15.750   1.5123   0.09386   0.08946  -0.0750   0.0103   1.0000
  16.000   1.4935   0.10199   0.09779  -0.0791   0.0102   1.0000
<< Back to S1091 (s1091-il)

Polar data table (+)

Polar graphs


<< Back to S1091 (s1091-il)