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OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: OAF117 AIRFOIL (oaf117-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.84 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oaf117-il-1000000.txt
Download as CSV file: xf-oaf117-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: OAF117 AIRFOIL                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -1.2517   0.07922   0.07628   0.0022   1.0000   0.0160
 -15.750  -1.2887   0.06971   0.06663  -0.0036   1.0000   0.0160
 -15.500  -1.3273   0.05997   0.05674  -0.0098   1.0000   0.0159
 -15.250  -1.3639   0.05024   0.04684  -0.0166   1.0000   0.0158
 -15.000  -1.3944   0.04068   0.03708  -0.0248   1.0000   0.0158
 -14.750  -1.3931   0.03314   0.02929  -0.0362   1.0000   0.0160
 -14.500  -1.3784   0.03089   0.02693  -0.0381   1.0000   0.0163
 -14.250  -1.3604   0.02922   0.02516  -0.0392   1.0000   0.0166
 -14.000  -1.3405   0.02782   0.02366  -0.0400   1.0000   0.0170
 -13.750  -1.3190   0.02660   0.02234  -0.0406   1.0000   0.0174
 -13.500  -1.2963   0.02555   0.02119  -0.0410   1.0000   0.0177
 -13.250  -1.2727   0.02459   0.02013  -0.0414   1.0000   0.0180
 -13.000  -1.2513   0.02294   0.01840  -0.0423   1.0000   0.0187
 -12.750  -1.2263   0.02209   0.01750  -0.0426   1.0000   0.0193
 -12.500  -1.2004   0.02140   0.01677  -0.0429   1.0000   0.0198
 -12.250  -1.1742   0.02074   0.01604  -0.0432   1.0000   0.0204
 -12.000  -1.1476   0.02010   0.01534  -0.0435   1.0000   0.0209
 -11.750  -1.1205   0.01958   0.01473  -0.0437   1.0000   0.0213
 -11.500  -1.0946   0.01841   0.01350  -0.0443   1.0000   0.0222
 -11.250  -1.0672   0.01780   0.01286  -0.0447   1.0000   0.0229
 -11.000  -1.0394   0.01729   0.01231  -0.0450   1.0000   0.0236
 -10.750  -1.0113   0.01683   0.01181  -0.0452   1.0000   0.0244
 -10.500  -0.9830   0.01647   0.01139  -0.0454   1.0000   0.0250
 -10.250  -0.9550   0.01567   0.01054  -0.0459   1.0000   0.0261
 -10.000  -0.9265   0.01517   0.01003  -0.0463   1.0000   0.0270
  -9.750  -0.8977   0.01477   0.00960  -0.0466   1.0000   0.0279
  -9.500  -0.8688   0.01443   0.00922  -0.0468   1.0000   0.0288
  -9.250  -0.8397   0.01403   0.00878  -0.0471   1.0000   0.0297
  -9.000  -0.8106   0.01343   0.00817  -0.0476   1.0000   0.0311
  -8.750  -0.7813   0.01308   0.00780  -0.0479   1.0000   0.0323
  -8.500  -0.7519   0.01277   0.00746  -0.0482   1.0000   0.0334
  -8.250  -0.7224   0.01246   0.00712  -0.0485   1.0000   0.0345
  -8.000  -0.6927   0.01196   0.00662  -0.0490   1.0000   0.0365
  -7.750  -0.6630   0.01166   0.00631  -0.0493   1.0000   0.0380
  -7.500  -0.6333   0.01140   0.00603  -0.0496   1.0000   0.0394
  -7.250  -0.6033   0.01100   0.00562  -0.0500   1.0000   0.0416
  -7.000  -0.5733   0.01070   0.00533  -0.0504   1.0000   0.0438
  -6.750  -0.5433   0.01047   0.00509  -0.0507   1.0000   0.0456
  -6.500  -0.5130   0.01012   0.00474  -0.0511   1.0000   0.0486
  -6.250  -0.4828   0.00985   0.00450  -0.0515   1.0000   0.0517
  -6.000  -0.4525   0.00959   0.00423  -0.0519   1.0000   0.0550
  -5.750  -0.4237   0.00952   0.00413  -0.0518   0.9373   0.0595
  -5.500  -0.3980   0.00943   0.00395  -0.0510   0.9036   0.0647
  -5.250  -0.3703   0.00929   0.00375  -0.0507   0.8762   0.0720
  -5.000  -0.3416   0.00910   0.00354  -0.0506   0.8510   0.0842
  -4.750  -0.3126   0.00892   0.00336  -0.0507   0.8255   0.1011
  -4.500  -0.2833   0.00879   0.00321  -0.0508   0.8009   0.1167
  -4.250  -0.2537   0.00869   0.00306  -0.0510   0.7776   0.1290
  -4.000  -0.2241   0.00860   0.00293  -0.0511   0.7565   0.1395
  -3.750  -0.1943   0.00851   0.00280  -0.0513   0.7360   0.1516
  -3.500  -0.1644   0.00842   0.00270  -0.0515   0.7157   0.1660
  -3.250  -0.1345   0.00836   0.00260  -0.0517   0.6960   0.1805
  -2.750  -0.0746   0.00822   0.00243  -0.0522   0.6594   0.2083
  -2.500  -0.0446   0.00815   0.00236  -0.0525   0.6436   0.2249
  -2.250  -0.0146   0.00809   0.00230  -0.0527   0.6285   0.2425
  -2.000   0.0154   0.00803   0.00225  -0.0530   0.6138   0.2619
  -1.750   0.0454   0.00796   0.00221  -0.0532   0.5999   0.2822
  -1.500   0.0754   0.00791   0.00218  -0.0535   0.5862   0.3060
  -1.250   0.1054   0.00789   0.00216  -0.0537   0.5725   0.3250
  -1.000   0.1353   0.00788   0.00214  -0.0539   0.5595   0.3408
  -0.750   0.1653   0.00786   0.00214  -0.0541   0.5471   0.3569
  -0.500   0.1952   0.00785   0.00213  -0.0543   0.5348   0.3721
  -0.250   0.2252   0.00786   0.00213  -0.0545   0.5223   0.3865
   0.250   0.2849   0.00789   0.00215  -0.0549   0.4952   0.4175
   0.500   0.3148   0.00791   0.00217  -0.0551   0.4815   0.4339
   0.750   0.3447   0.00793   0.00220  -0.0553   0.4692   0.4519
   1.000   0.3745   0.00796   0.00223  -0.0555   0.4569   0.4690
   1.250   0.4044   0.00798   0.00227  -0.0557   0.4449   0.4874
   1.500   0.4342   0.00800   0.00232  -0.0559   0.4337   0.5085
   1.750   0.4640   0.00804   0.00238  -0.0561   0.4218   0.5306
   2.000   0.4938   0.00807   0.00243  -0.0564   0.4100   0.5534
   2.250   0.5236   0.00808   0.00250  -0.0566   0.3987   0.5828
   2.500   0.5533   0.00810   0.00259  -0.0568   0.3869   0.6200
   2.750   0.5830   0.00811   0.00268  -0.0570   0.3748   0.6624
   3.000   0.6126   0.00808   0.00278  -0.0572   0.3627   0.7136
   3.250   0.6416   0.00801   0.00290  -0.0573   0.3510   0.7897
   3.500   0.6633   0.00767   0.00291  -0.0555   0.3393   0.9403
   3.750   0.6923   0.00774   0.00293  -0.0555   0.3256   1.0000
   4.000   0.7219   0.00791   0.00304  -0.0557   0.3105   1.0000
   4.250   0.7514   0.00812   0.00316  -0.0559   0.2929   1.0000
   4.500   0.7808   0.00833   0.00329  -0.0561   0.2768   1.0000
   4.750   0.8102   0.00854   0.00344  -0.0563   0.2626   1.0000
   5.000   0.8395   0.00874   0.00359  -0.0565   0.2486   1.0000
   5.250   0.8687   0.00898   0.00376  -0.0567   0.2314   1.0000
   5.500   0.8977   0.00927   0.00394  -0.0569   0.2118   1.0000
   5.750   0.9267   0.00957   0.00415  -0.0571   0.1927   1.0000
   6.000   0.9554   0.00989   0.00438  -0.0573   0.1756   1.0000
   6.250   0.9842   0.01020   0.00462  -0.0574   0.1613   1.0000
   6.500   1.0128   0.01052   0.00488  -0.0576   0.1472   1.0000
   6.750   1.0413   0.01085   0.00514  -0.0577   0.1336   1.0000
   7.000   1.0696   0.01120   0.00542  -0.0579   0.1203   1.0000
   7.250   1.0977   0.01159   0.00573  -0.0580   0.1058   1.0000
   7.500   1.1255   0.01204   0.00607  -0.0581   0.0908   1.0000
   7.750   1.1531   0.01250   0.00645  -0.0581   0.0772   1.0000
   8.000   1.1805   0.01296   0.00684  -0.0582   0.0661   1.0000
   8.250   1.2078   0.01343   0.00726  -0.0582   0.0572   1.0000
   8.500   1.2348   0.01391   0.00770  -0.0582   0.0504   1.0000
   8.750   1.2618   0.01435   0.00812  -0.0582   0.0459   1.0000
   9.000   1.2887   0.01479   0.00856  -0.0581   0.0423   1.0000
   9.250   1.3152   0.01526   0.00902  -0.0580   0.0394   1.0000
   9.500   1.3415   0.01575   0.00952  -0.0578   0.0368   1.0000
   9.750   1.3678   0.01618   0.00996  -0.0577   0.0349   1.0000
  10.000   1.3931   0.01679   0.01057  -0.0575   0.0326   1.0000
  10.250   1.4188   0.01725   0.01107  -0.0573   0.0313   1.0000
  10.500   1.4443   0.01771   0.01156  -0.0570   0.0301   1.0000
  10.750   1.4689   0.01828   0.01215  -0.0567   0.0288   1.0000
  11.000   1.4916   0.01910   0.01300  -0.0562   0.0273   1.0000
  11.250   1.5162   0.01958   0.01353  -0.0559   0.0267   1.0000
  11.500   1.5399   0.02013   0.01412  -0.0555   0.0259   1.0000
  11.750   1.5629   0.02073   0.01476  -0.0550   0.0251   1.0000
  12.000   1.5844   0.02147   0.01553  -0.0544   0.0242   1.0000
  12.250   1.6021   0.02261   0.01672  -0.0534   0.0232   1.0000
  12.500   1.6235   0.02322   0.01739  -0.0527   0.0228   1.0000
  12.750   1.6434   0.02394   0.01817  -0.0519   0.0223   1.0000
  13.000   1.6618   0.02474   0.01904  -0.0509   0.0218   1.0000
  13.250   1.6786   0.02561   0.01996  -0.0498   0.0213   1.0000
  13.500   1.6929   0.02657   0.02098  -0.0484   0.0209   1.0000
  13.750   1.7030   0.02774   0.02221  -0.0466   0.0205   1.0000
  14.000   1.7046   0.02926   0.02381  -0.0440   0.0201   1.0000
  14.250   1.6986   0.03163   0.02629  -0.0418   0.0198   1.0000
  14.500   1.6919   0.03482   0.02960  -0.0412   0.0195   1.0000
  14.750   1.6963   0.03721   0.03210  -0.0413   0.0194   1.0000
  15.000   1.6991   0.04000   0.03500  -0.0418   0.0192   1.0000
  15.250   1.6994   0.04322   0.03833  -0.0425   0.0190   1.0000
  15.500   1.6976   0.04684   0.04206  -0.0435   0.0188   1.0000
  15.750   1.6935   0.05082   0.04615  -0.0447   0.0186   1.0000
  16.000   1.6867   0.05522   0.05066  -0.0461   0.0184   1.0000
  16.250   1.6779   0.05992   0.05548  -0.0476   0.0183   1.0000
  16.500   1.6659   0.06511   0.06078  -0.0493   0.0181   1.0000
  16.750   1.6520   0.07061   0.06640  -0.0511   0.0180   1.0000
  17.000   1.6362   0.07639   0.07229  -0.0531   0.0179   1.0000
  17.250   1.6196   0.08248   0.07849  -0.0553   0.0178   1.0000
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