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St. CYR 171 (Royer) (stcyr171-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: St. CYR 171 (Royer) (stcyr171-il)
Reynolds number: 200,000
Max Cl/Cd: 47.55 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-stcyr171-il-200000.txt
Download as CSV file: xf-stcyr171-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: St. CYR 171 (Royer)                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.8886   0.07698   0.07252  -0.0375   1.0000   0.0458
 -13.500  -0.9255   0.06850   0.06388  -0.0432   1.0000   0.0455
 -13.250  -0.9528   0.06165   0.05688  -0.0478   1.0000   0.0452
 -13.000  -0.9781   0.05569   0.05073  -0.0516   1.0000   0.0450
 -12.750  -1.0013   0.05109   0.04590  -0.0531   1.0000   0.0450
 -12.500  -1.0193   0.04769   0.04229  -0.0519   1.0000   0.0450
 -12.250  -1.0333   0.04499   0.03937  -0.0491   1.0000   0.0450
 -12.000  -1.0421   0.04256   0.03670  -0.0460   1.0000   0.0452
 -11.750  -1.0445   0.04041   0.03427  -0.0434   1.0000   0.0456
 -11.500  -1.0424   0.03854   0.03213  -0.0408   1.0000   0.0460
 -11.250  -1.0395   0.03557   0.02898  -0.0384   1.0000   0.0467
 -11.000  -1.0298   0.03369   0.02703  -0.0363   1.0000   0.0475
 -10.750  -1.0183   0.03219   0.02544  -0.0342   1.0000   0.0483
 -10.500  -1.0061   0.03078   0.02393  -0.0321   1.0000   0.0490
 -10.250  -0.9930   0.02947   0.02251  -0.0300   1.0000   0.0497
 -10.000  -0.9792   0.02825   0.02118  -0.0279   1.0000   0.0506
  -9.750  -0.9647   0.02715   0.01995  -0.0259   1.0000   0.0517
  -9.500  -0.9495   0.02613   0.01881  -0.0238   1.0000   0.0529
  -9.250  -0.9337   0.02519   0.01774  -0.0218   1.0000   0.0538
  -9.000  -0.9212   0.02403   0.01656  -0.0192   1.0000   0.0549
  -8.750  -0.9073   0.02307   0.01560  -0.0168   1.0000   0.0561
  -8.500  -0.8915   0.02227   0.01477  -0.0147   1.0000   0.0576
  -8.250  -0.8747   0.02154   0.01400  -0.0126   1.0000   0.0594
  -8.000  -0.8569   0.02089   0.01328  -0.0107   1.0000   0.0617
  -7.750  -0.8400   0.02019   0.01254  -0.0087   1.0000   0.0643
  -7.500  -0.8225   0.01952   0.01190  -0.0068   1.0000   0.0680
  -7.250  -0.8037   0.01896   0.01129  -0.0050   1.0000   0.0727
  -7.000  -0.7856   0.01833   0.01075  -0.0031   1.0000   0.0813
  -6.750  -0.7663   0.01778   0.01030  -0.0014   1.0000   0.0992
  -6.500  -0.7438   0.01745   0.01005  -0.0004   1.0000   0.1215
  -6.250  -0.7202   0.01725   0.00984   0.0004   1.0000   0.1362
  -6.000  -0.6976   0.01704   0.00960   0.0015   1.0000   0.1463
  -5.750  -0.6749   0.01687   0.00939   0.0025   1.0000   0.1546
  -5.500  -0.6536   0.01662   0.00912   0.0038   1.0000   0.1618
  -5.250  -0.6322   0.01642   0.00892   0.0050   1.0000   0.1685
  -5.000  -0.6103   0.01624   0.00866   0.0062   1.0000   0.1745
  -4.750  -0.5909   0.01597   0.00844   0.0079   1.0000   0.1803
  -4.500  -0.5697   0.01582   0.00829   0.0091   1.0000   0.1877
  -4.250  -0.5495   0.01564   0.00810   0.0106   1.0000   0.1943
  -4.000  -0.5299   0.01549   0.00800   0.0121   1.0000   0.2006
  -3.750  -0.5100   0.01539   0.00786   0.0136   1.0000   0.2076
  -3.500  -0.4917   0.01528   0.00780   0.0152   1.0000   0.2144
  -3.250  -0.4731   0.01524   0.00777   0.0168   1.0000   0.2232
  -3.000  -0.4382   0.01518   0.00776   0.0150   0.9958   0.2351
  -2.750  -0.3964   0.01509   0.00772   0.0119   0.9890   0.2503
  -2.500  -0.3539   0.01508   0.00779   0.0089   0.9821   0.2669
  -2.250  -0.3150   0.01514   0.00796   0.0067   0.9732   0.2839
  -2.000  -0.2706   0.01548   0.00851   0.0035   0.9669   0.3067
  -1.750  -0.2312   0.01691   0.01050   0.0021   0.9560   0.3355
  -1.500  -0.1795   0.01885   0.01235  -0.0016   0.9472   0.4221
  -1.250  -0.1311   0.01926   0.01282  -0.0049   0.9373   0.4387
  -1.000  -0.0900   0.01931   0.01286  -0.0068   0.9248   0.4573
  -0.750  -0.0521   0.01839   0.01193  -0.0086   0.9132   0.4869
  -0.500  -0.0247   0.01536   0.00879  -0.0091   0.9001   0.5375
  -0.250   0.0070   0.01379   0.00713  -0.0100   0.8826   0.5579
   0.000   0.0402   0.01263   0.00591  -0.0109   0.8616   0.5709
   0.250   0.0716   0.01195   0.00518  -0.0113   0.8361   0.5803
   0.500   0.1035   0.01127   0.00450  -0.0118   0.8120   0.5897
   0.750   0.1345   0.01073   0.00405  -0.0122   0.7877   0.5981
   1.000   0.1627   0.01039   0.00382  -0.0119   0.7611   0.6059
   1.250   0.1888   0.01018   0.00371  -0.0111   0.7352   0.6143
   1.500   0.2112   0.01007   0.00380  -0.0095   0.7090   0.6268
   1.750   0.2329   0.01012   0.00398  -0.0076   0.6804   0.6464
   2.000   0.2562   0.01022   0.00403  -0.0063   0.6453   0.6667
   2.500   0.3008   0.01062   0.00403  -0.0032   0.5408   0.6845
   2.750   0.3202   0.01107   0.00411  -0.0012   0.4593   0.6924
   3.000   0.3361   0.01176   0.00423   0.0011   0.3398   0.6989
   3.250   0.3563   0.01238   0.00453   0.0025   0.2958   0.7049
   3.500   0.3795   0.01281   0.00483   0.0034   0.2727   0.7098
   3.750   0.4032   0.01321   0.00514   0.0043   0.2571   0.7151
   4.000   0.4275   0.01359   0.00544   0.0050   0.2440   0.7204
   4.250   0.4527   0.01390   0.00577   0.0056   0.2331   0.7248
   4.500   0.4772   0.01431   0.00610   0.0063   0.2225   0.7293
   4.750   0.5027   0.01452   0.00637   0.0068   0.2126   0.7347
   5.000   0.5275   0.01496   0.00675   0.0074   0.2043   0.7389
   5.250   0.5534   0.01520   0.00707   0.0079   0.1972   0.7419
   5.500   0.5787   0.01557   0.00742   0.0083   0.1904   0.7459
   5.750   0.6044   0.01592   0.00784   0.0088   0.1842   0.7505
   6.000   0.6301   0.01617   0.00817   0.0092   0.1778   0.7566
   6.250   0.6554   0.01661   0.00859   0.0096   0.1707   0.7664
   6.500   0.6809   0.01660   0.00881   0.0102   0.1633   0.7776
   6.750   0.7067   0.01675   0.00909   0.0105   0.1560   0.7985
   7.000   0.7391   0.01691   0.00949   0.0096   0.1475   0.8353
   7.250   0.7687   0.01714   0.00974   0.0090   0.1373   0.8588
   7.500   0.7976   0.01717   0.00989   0.0088   0.1225   0.8743
   7.750   0.8255   0.01736   0.01012   0.0087   0.0978   0.8855
   8.000   0.8485   0.01810   0.01072   0.0093   0.0804   0.8936
   8.250   0.8695   0.01884   0.01143   0.0104   0.0723   0.8970
   8.500   0.8874   0.01963   0.01224   0.0122   0.0682   0.8956
   8.750   0.9159   0.02048   0.01316   0.0116   0.0642   0.9131
   9.000   0.9257   0.02125   0.01389   0.0148   0.0618   0.8995
   9.250   0.9331   0.02213   0.01475   0.0186   0.0600   0.8781
   9.500   0.9432   0.02284   0.01551   0.0219   0.0583   0.8492
   9.750   0.9563   0.02371   0.01641   0.0244   0.0568   0.8247
  10.000   0.9716   0.02469   0.01739   0.0263   0.0554   0.8083
  10.250   0.9879   0.02576   0.01845   0.0279   0.0541   0.7964
  10.500   1.0044   0.02710   0.01970   0.0293   0.0527   0.7815
  10.750   1.0217   0.02892   0.02154   0.0304   0.0514   0.7713
  11.000   1.0368   0.03010   0.02288   0.0320   0.0504   0.7666
  11.250   1.0510   0.03154   0.02448   0.0336   0.0495   0.7626
  11.500   1.0636   0.03306   0.02615   0.0353   0.0487   0.7591
  11.750   1.0732   0.03468   0.02793   0.0374   0.0479   0.7561
  12.000   1.0795   0.03626   0.02967   0.0398   0.0472   0.7538
  12.250   1.0846   0.03785   0.03138   0.0422   0.0464   0.7517
  12.500   1.0896   0.03954   0.03317   0.0443   0.0457   0.7496
  12.750   1.0937   0.04159   0.03530   0.0462   0.0450   0.7474
  13.000   1.0949   0.04433   0.03815   0.0477   0.0442   0.7454
  13.250   1.0846   0.04771   0.04176   0.0497   0.0439   0.7441
  13.500   1.0702   0.05084   0.04510   0.0514   0.0438   0.7427
  13.750   1.0522   0.05421   0.04870   0.0522   0.0437   0.7416
  14.000   1.0352   0.05817   0.05286   0.0518   0.0437   0.7406
  14.500   0.9894   0.06870   0.06381   0.0476   0.0438   0.7388
  14.750   0.9624   0.07518   0.07050   0.0431   0.0441   0.7385
  15.000   0.6308   0.16220   0.15834  -0.0110   0.0776   0.7937
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