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

E197 (13.49%) (e197-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E197 (13.49%) (e197-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.9 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e197-il-1000000.txt
Download as CSV file: xf-e197-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E197  (13.49%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.6981   0.07169   0.06961  -0.0546   1.0000   0.0095
 -13.500  -0.7231   0.06281   0.06059  -0.0610   1.0000   0.0095
 -13.250  -0.7438   0.05549   0.05313  -0.0665   1.0000   0.0095
 -13.000  -0.7748   0.04734   0.04478  -0.0724   1.0000   0.0093
 -12.750  -0.7832   0.04305   0.04035  -0.0755   1.0000   0.0094
 -12.500  -0.7916   0.03934   0.03650  -0.0778   1.0000   0.0095
 -12.250  -0.8107   0.03521   0.03217  -0.0788   1.0000   0.0095
 -12.000  -0.8182   0.03311   0.02994  -0.0777   1.0000   0.0096
 -11.750  -0.8264   0.03166   0.02839  -0.0748   1.0000   0.0096
 -11.500  -0.8299   0.03114   0.02779  -0.0708   1.0000   0.0097
 -11.250  -0.8374   0.02948   0.02598  -0.0669   1.0000   0.0097
 -11.000  -0.8269   0.02659   0.02279  -0.0673   0.9961   0.0100
 -10.750  -0.8092   0.02344   0.01938  -0.0687   0.9893   0.0103
 -10.500  -0.7793   0.02215   0.01804  -0.0707   0.9847   0.0107
 -10.250  -0.7503   0.02105   0.01684  -0.0722   0.9764   0.0110
 -10.000  -0.7198   0.02009   0.01578  -0.0738   0.9648   0.0113
  -9.750  -0.6907   0.01916   0.01473  -0.0749   0.9448   0.0117
  -9.500  -0.6676   0.01842   0.01383  -0.0745   0.9137   0.0120
  -9.000  -0.6280   0.01729   0.01230  -0.0721   0.8561   0.0127
  -8.750  -0.6061   0.01691   0.01176  -0.0712   0.8341   0.0129
  -8.500  -0.5841   0.01642   0.01112  -0.0703   0.8148   0.0131
  -8.250  -0.5672   0.01505   0.00956  -0.0688   0.7980   0.0135
  -8.000  -0.5477   0.01411   0.00850  -0.0677   0.7831   0.0140
  -7.750  -0.5253   0.01354   0.00783  -0.0670   0.7696   0.0144
  -7.500  -0.5017   0.01311   0.00731  -0.0664   0.7574   0.0149
  -7.000  -0.4526   0.01236   0.00639  -0.0654   0.7359   0.0160
  -6.750  -0.4277   0.01199   0.00594  -0.0650   0.7266   0.0165
  -6.500  -0.4025   0.01165   0.00550  -0.0646   0.7178   0.0169
  -6.250  -0.3766   0.01136   0.00515  -0.0643   0.7100   0.0172
  -6.000  -0.3527   0.01080   0.00447  -0.0636   0.7024   0.0180
  -5.750  -0.3271   0.01043   0.00403  -0.0633   0.6955   0.0191
  -5.500  -0.3008   0.01017   0.00371  -0.0631   0.6887   0.0202
  -5.250  -0.2741   0.00994   0.00343  -0.0629   0.6829   0.0215
  -5.000  -0.2473   0.00972   0.00315  -0.0627   0.6767   0.0232
  -4.750  -0.2209   0.00947   0.00287  -0.0624   0.6711   0.0278
  -4.500  -0.1951   0.00904   0.00258  -0.0622   0.6660   0.0558
  -4.250  -0.1691   0.00870   0.00237  -0.0620   0.6608   0.0879
  -4.000  -0.1427   0.00846   0.00220  -0.0618   0.6558   0.1179
  -3.750  -0.1158   0.00818   0.00204  -0.0618   0.6513   0.1527
  -3.500  -0.0895   0.00787   0.00189  -0.0617   0.6466   0.1986
  -3.250  -0.0629   0.00764   0.00176  -0.0615   0.6420   0.2414
  -3.000  -0.0361   0.00739   0.00165  -0.0615   0.6379   0.2864
  -2.750  -0.0094   0.00711   0.00156  -0.0614   0.6336   0.3415
  -2.500   0.0175   0.00692   0.00150  -0.0613   0.6294   0.3920
  -2.250   0.0449   0.00683   0.00147  -0.0613   0.6252   0.4274
  -2.000   0.0730   0.00674   0.00144  -0.0613   0.6214   0.4532
  -1.750   0.1010   0.00667   0.00141  -0.0614   0.6174   0.4740
  -1.500   0.1289   0.00664   0.00138  -0.0614   0.6134   0.4949
  -1.250   0.1570   0.00662   0.00137  -0.0614   0.6095   0.5104
  -1.000   0.1854   0.00657   0.00136  -0.0615   0.6058   0.5247
  -0.750   0.2136   0.00653   0.00134  -0.0616   0.6019   0.5400
  -0.500   0.2415   0.00652   0.00134  -0.0616   0.5980   0.5556
  -0.250   0.2696   0.00651   0.00135  -0.0617   0.5942   0.5723
   0.000   0.2978   0.00646   0.00135  -0.0617   0.5906   0.5901
   0.250   0.3258   0.00642   0.00136  -0.0618   0.5867   0.6089
   0.500   0.3535   0.00641   0.00138  -0.0617   0.5827   0.6288
   1.000   0.4091   0.00632   0.00144  -0.0617   0.5752   0.6774
   1.250   0.4364   0.00627   0.00147  -0.0616   0.5711   0.7067
   1.500   0.4633   0.00624   0.00151  -0.0614   0.5670   0.7394
   1.750   0.4903   0.00617   0.00157  -0.0612   0.5631   0.7747
   2.000   0.5168   0.00608   0.00162  -0.0609   0.5589   0.8131
   2.250   0.5424   0.00603   0.00168  -0.0603   0.5544   0.8546
   2.500   0.5673   0.00598   0.00176  -0.0595   0.5496   0.9004
   2.750   0.5955   0.00596   0.00183  -0.0594   0.5441   0.9414
   3.000   0.6294   0.00604   0.00190  -0.0606   0.5379   0.9648
   3.250   0.6655   0.00609   0.00196  -0.0625   0.5317   0.9774
   3.500   0.7022   0.00616   0.00202  -0.0644   0.5249   0.9855
   3.750   0.7408   0.00623   0.00209  -0.0669   0.5179   0.9907
   4.000   0.7782   0.00631   0.00215  -0.0690   0.5100   0.9954
   4.250   0.8171   0.00638   0.00221  -0.0716   0.5020   0.9992
   4.500   0.8448   0.00648   0.00229  -0.0717   0.4935   1.0000
   4.750   0.8690   0.00656   0.00238  -0.0710   0.4847   1.0000
   5.000   0.8925   0.00668   0.00247  -0.0702   0.4753   1.0000
   5.250   0.9162   0.00680   0.00258  -0.0694   0.4648   1.0000
   5.500   0.9402   0.00693   0.00270  -0.0687   0.4537   1.0000
   5.750   0.9635   0.00709   0.00283  -0.0679   0.4394   1.0000
   6.000   0.9859   0.00731   0.00299  -0.0669   0.4211   1.0000
   6.250   1.0083   0.00755   0.00317  -0.0660   0.3997   1.0000
   6.500   1.0284   0.00794   0.00342  -0.0647   0.3661   1.0000
   6.750   1.0466   0.00847   0.00375  -0.0631   0.3227   1.0000
   7.000   1.0620   0.00919   0.00420  -0.0611   0.2703   1.0000
   7.250   1.0785   0.00985   0.00465  -0.0593   0.2289   1.0000
   7.500   1.0939   0.01057   0.00515  -0.0574   0.1874   1.0000
   7.750   1.1101   0.01121   0.00562  -0.0557   0.1540   1.0000
   8.000   1.1259   0.01186   0.00610  -0.0538   0.1250   1.0000
   8.250   1.1414   0.01248   0.00659  -0.0520   0.1008   1.0000
   8.500   1.1560   0.01311   0.00710  -0.0500   0.0805   1.0000
   8.750   1.1713   0.01366   0.00759  -0.0481   0.0657   1.0000
   9.000   1.1849   0.01420   0.00807  -0.0459   0.0543   1.0000
   9.250   1.1946   0.01477   0.00860  -0.0430   0.0436   1.0000
   9.500   1.2032   0.01543   0.00920  -0.0400   0.0336   1.0000
   9.750   1.2085   0.01628   0.00997  -0.0367   0.0221   1.0000
  10.000   1.2131   0.01723   0.01088  -0.0336   0.0135   1.0000
  10.250   1.2212   0.01810   0.01176  -0.0311   0.0107   1.0000
  10.500   1.2301   0.01899   0.01270  -0.0289   0.0093   1.0000
  10.750   1.2398   0.01989   0.01364  -0.0271   0.0086   1.0000
  11.000   1.2487   0.02091   0.01470  -0.0253   0.0081   1.0000
  11.250   1.2536   0.02226   0.01612  -0.0232   0.0075   1.0000
  11.500   1.2622   0.02344   0.01737  -0.0217   0.0073   1.0000
  11.750   1.2716   0.02463   0.01861  -0.0205   0.0070   1.0000
  12.000   1.2788   0.02603   0.02009  -0.0191   0.0067   1.0000
  12.250   1.2881   0.02732   0.02143  -0.0181   0.0065   1.0000
  12.500   1.2946   0.02888   0.02306  -0.0170   0.0064   1.0000
  12.750   1.3002   0.03057   0.02481  -0.0160   0.0062   1.0000
  13.000   1.3038   0.03247   0.02677  -0.0150   0.0058   1.0000
  13.250   1.3090   0.03428   0.02866  -0.0142   0.0058   1.0000
  13.500   1.3050   0.03700   0.03147  -0.0132   0.0055   1.0000
  13.750   1.3097   0.03895   0.03349  -0.0126   0.0056   1.0000
  14.000   1.3009   0.04230   0.03696  -0.0118   0.0054   1.0000
  14.250   1.2973   0.04525   0.04001  -0.0113   0.0053   1.0000
  14.500   1.2975   0.04790   0.04274  -0.0110   0.0053   1.0000
  14.750   1.3034   0.05001   0.04492  -0.0109   0.0052   1.0000
  15.000   1.3030   0.05287   0.04788  -0.0109   0.0052   1.0000
  15.250   1.3032   0.05574   0.05084  -0.0110   0.0051   1.0000
  15.500   1.3048   0.05854   0.05371  -0.0112   0.0051   1.0000
  15.750   1.3049   0.06160   0.05686  -0.0115   0.0050   1.0000
  16.000   1.3017   0.06511   0.06047  -0.0120   0.0050   1.0000
  16.250   1.3026   0.06823   0.06368  -0.0126   0.0049   1.0000
  16.500   1.2980   0.07213   0.06768  -0.0134   0.0049   1.0000
  16.750   1.2984   0.07548   0.07110  -0.0143   0.0048   1.0000
  17.000   1.2949   0.07944   0.07516  -0.0153   0.0047   1.0000
  17.250   1.2905   0.08360   0.07942  -0.0165   0.0047   1.0000
  17.500   1.2861   0.08788   0.08380  -0.0179   0.0047   1.0000
  17.750   1.2833   0.09202   0.08804  -0.0194   0.0047   1.0000
  18.000   1.2788   0.09650   0.09261  -0.0211   0.0046   1.0000
  18.250   1.2720   0.10141   0.09763  -0.0230   0.0046   1.0000
  18.500   1.2667   0.10624   0.10257  -0.0250   0.0046   1.0000
  18.750   1.2606   0.11130   0.10774  -0.0273   0.0045   1.0000
  19.000   1.2535   0.11656   0.11312  -0.0297   0.0045   1.0000
<< Back to E197 (13.49%) (e197-il)

Polar data table (+)

Polar graphs


<< Back to E197 (13.49%) (e197-il)