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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 200,000
Max Cl/Cd: 69.65 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-isa571-il-200000.txt
Download as CSV file: xf-isa571-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 571                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4183   0.10682   0.10329  -0.0230   1.0000   0.0347
  -9.000  -0.4217   0.10435   0.10088  -0.0240   1.0000   0.0347
  -8.750  -0.4238   0.10160   0.09819  -0.0252   1.0000   0.0348
  -8.500  -0.4234   0.09534   0.09196  -0.0228   1.0000   0.0355
  -8.250  -0.4163   0.09171   0.08835  -0.0205   1.0000   0.0361
  -8.000  -0.4139   0.08880   0.08545  -0.0196   1.0000   0.0367
  -7.750  -0.4118   0.08589   0.08258  -0.0197   1.0000   0.0373
  -7.500  -0.4098   0.08294   0.07967  -0.0203   1.0000   0.0380
  -7.250  -0.4069   0.07988   0.07663  -0.0214   1.0000   0.0388
  -7.000  -0.4027   0.07666   0.07344  -0.0228   1.0000   0.0397
  -6.750  -0.3964   0.07328   0.07005  -0.0247   1.0000   0.0408
  -6.500  -0.3874   0.06965   0.06641  -0.0272   1.0000   0.0423
  -6.250  -0.3643   0.06548   0.06207  -0.0346   1.0000   0.0451
  -6.000  -0.3436   0.06180   0.05816  -0.0382   1.0000   0.0456
  -5.750  -0.3265   0.05807   0.05424  -0.0395   1.0000   0.0458
  -5.500  -0.3214   0.05158   0.04783  -0.0398   1.0000   0.0470
  -5.250  -0.3098   0.04914   0.04544  -0.0387   1.0000   0.0486
  -5.000  -0.2934   0.04679   0.04304  -0.0386   1.0000   0.0520
  -4.750  -0.2564   0.04440   0.03995  -0.0414   1.0000   0.0581
  -4.500  -0.2413   0.03866   0.03426  -0.0425   1.0000   0.0600
  -4.250  -0.2226   0.03648   0.03207  -0.0423   1.0000   0.0624
  -4.000  -0.1936   0.03359   0.02869  -0.0434   1.0000   0.0721
  -3.750  -0.1740   0.03172   0.02691  -0.0431   1.0000   0.0760
  -3.500  -0.1303   0.02504   0.01914  -0.0451   1.0000   0.0600
  -3.250  -0.0958   0.02168   0.01532  -0.0459   1.0000   0.0551
  -3.000  -0.0548   0.01928   0.01238  -0.0484   0.9981   0.0612
  -2.750  -0.0104   0.01807   0.01093  -0.0516   0.9946   0.0676
  -2.500   0.0318   0.01680   0.00941  -0.0544   0.9902   0.0736
  -2.250   0.0760   0.01629   0.00879  -0.0576   0.9851   0.0807
  -2.000   0.1180   0.01540   0.00779  -0.0603   0.9792   0.0844
  -1.750   0.1618   0.01479   0.00722  -0.0636   0.9729   0.0906
  -1.500   0.2023   0.01420   0.00658  -0.0659   0.9650   0.0951
  -1.250   0.2458   0.01346   0.00594  -0.0690   0.9587   0.1015
  -1.000   0.2846   0.01287   0.00542  -0.0711   0.9489   0.1128
  -0.750   0.3278   0.01207   0.00475  -0.0740   0.9408   0.1386
  -0.250   0.3993   0.00901   0.00401  -0.0762   0.9161   1.0000
   0.000   0.4330   0.00876   0.00365  -0.0767   0.8920   1.0000
   0.250   0.4699   0.00852   0.00327  -0.0779   0.8613   1.0000
   0.500   0.5062   0.00837   0.00293  -0.0789   0.8160   1.0000
   0.750   0.5367   0.00847   0.00271  -0.0787   0.7553   1.0000
   1.000   0.5620   0.00881   0.00267  -0.0777   0.6951   1.0000
   1.250   0.5857   0.00923   0.00273  -0.0765   0.6422   1.0000
   1.500   0.6093   0.00964   0.00285  -0.0755   0.5941   1.0000
   1.750   0.6331   0.01003   0.00299  -0.0746   0.5512   1.0000
   2.000   0.6575   0.01039   0.00313  -0.0739   0.5162   1.0000
   2.250   0.6825   0.01073   0.00330  -0.0733   0.4892   1.0000
   2.500   0.7076   0.01108   0.00348  -0.0728   0.4673   1.0000
   2.750   0.7331   0.01141   0.00371  -0.0724   0.4480   1.0000
   3.000   0.7587   0.01173   0.00393  -0.0720   0.4319   1.0000
   3.250   0.7846   0.01204   0.00419  -0.0716   0.4186   1.0000
   3.500   0.8106   0.01237   0.00446  -0.0713   0.4068   1.0000
   3.750   0.8365   0.01270   0.00476  -0.0710   0.3957   1.0000
   4.000   0.8624   0.01301   0.00505  -0.0707   0.3838   1.0000
   4.250   0.8883   0.01329   0.00536  -0.0704   0.3717   1.0000
   4.500   0.9140   0.01360   0.00569  -0.0701   0.3600   1.0000
   4.750   0.9395   0.01391   0.00604  -0.0697   0.3475   1.0000
   5.000   0.9647   0.01422   0.00637  -0.0693   0.3344   1.0000
   5.250   0.9898   0.01454   0.00672  -0.0688   0.3209   1.0000
   5.500   1.0144   0.01481   0.00704  -0.0683   0.3042   1.0000
   5.750   1.0385   0.01505   0.00731  -0.0677   0.2839   1.0000
   6.000   1.0627   0.01530   0.00760  -0.0672   0.2627   1.0000
   6.250   1.0865   0.01560   0.00789  -0.0666   0.2398   1.0000
   6.500   1.1102   0.01597   0.00825  -0.0661   0.2150   1.0000
   6.750   1.1327   0.01650   0.00871  -0.0654   0.1892   1.0000
   7.000   1.1544   0.01717   0.00932  -0.0646   0.1633   1.0000
   7.250   1.1742   0.01813   0.00998  -0.0636   0.1015   1.0000
   7.500   1.1875   0.02002   0.01136  -0.0616   0.0430   1.0000
   7.750   1.2045   0.02140   0.01274  -0.0599   0.0346   1.0000
   8.000   1.2221   0.02254   0.01407  -0.0583   0.0311   1.0000
   8.250   1.2360   0.02400   0.01567  -0.0563   0.0281   1.0000
   8.500   1.2448   0.02587   0.01771  -0.0536   0.0265   1.0000
   8.750   1.2562   0.02748   0.01944  -0.0512   0.0258   1.0000
   9.000   1.2683   0.02902   0.02112  -0.0489   0.0252   1.0000
   9.250   1.2799   0.03072   0.02296  -0.0466   0.0246   1.0000
   9.500   1.2916   0.03254   0.02492  -0.0444   0.0241   1.0000
   9.750   1.3031   0.03435   0.02687  -0.0424   0.0232   1.0000
  10.000   1.3130   0.03617   0.02882  -0.0402   0.0221   1.0000
  10.250   1.3216   0.03821   0.03100  -0.0379   0.0214   1.0000
  10.500   1.3299   0.04056   0.03357  -0.0357   0.0212   1.0000
  10.750   1.3359   0.04310   0.03634  -0.0333   0.0210   1.0000
  11.000   1.3387   0.04584   0.03935  -0.0308   0.0211   1.0000
  11.250   1.3376   0.04883   0.04263  -0.0281   0.0212   1.0000
  11.500   1.3299   0.05212   0.04625  -0.0254   0.0215   1.0000
  11.750   1.3188   0.05583   0.05028  -0.0233   0.0219   1.0000
  12.000   1.3043   0.05999   0.05476  -0.0219   0.0222   1.0000
  12.250   1.2875   0.06469   0.05975  -0.0216   0.0226   1.0000
  12.500   1.2692   0.06997   0.06530  -0.0226   0.0229   1.0000
  12.750   1.2498   0.07594   0.07151  -0.0248   0.0232   1.0000
  13.000   1.2295   0.08257   0.07837  -0.0281   0.0234   1.0000
  13.250   1.2085   0.08988   0.08588  -0.0323   0.0237   1.0000
  13.500   1.1868   0.09784   0.09402  -0.0373   0.0239   1.0000
  13.750   1.1644   0.10651   0.10286  -0.0429   0.0240   1.0000
  14.000   1.1408   0.11600   0.11250  -0.0492   0.0242   1.0000
  14.250   1.1165   0.12631   0.12294  -0.0560   0.0244   1.0000
  14.500   1.0898   0.13821   0.13492  -0.0637   0.0248   1.0000
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