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RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il)
Reynolds number: 500,000
Max Cl/Cd: 102.18 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r1080-il-500000-n5.txt
Download as CSV file: xf-r1080-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.5409   0.08963   0.08558  -0.0927   0.7597   0.0086
 -16.250  -0.5726   0.07915   0.07485  -0.0990   0.7551   0.0085
 -16.000  -0.5973   0.07072   0.06622  -0.1042   0.7491   0.0085
 -15.750  -0.6194   0.06344   0.05874  -0.1087   0.7425   0.0085
 -15.500  -0.6321   0.05819   0.05329  -0.1116   0.7359   0.0084
 -15.250  -0.6430   0.05370   0.04865  -0.1138   0.7294   0.0084
 -15.000  -0.6576   0.04923   0.04398  -0.1154   0.7232   0.0085
 -14.750  -0.6677   0.04567   0.04024  -0.1161   0.7177   0.0085
 -14.500  -0.6732   0.04286   0.03727  -0.1162   0.7122   0.0085
 -14.250  -0.6792   0.04019   0.03444  -0.1157   0.7070   0.0086
 -14.000  -0.6814   0.03804   0.03216  -0.1151   0.7021   0.0086
 -13.750  -0.6814   0.03614   0.03014  -0.1142   0.6978   0.0087
 -13.500  -0.6803   0.03438   0.02826  -0.1131   0.6932   0.0088
 -13.250  -0.6756   0.03301   0.02679  -0.1119   0.6891   0.0089
 -13.000  -0.6733   0.03139   0.02502  -0.1104   0.6854   0.0089
 -12.750  -0.6663   0.03021   0.02375  -0.1092   0.6821   0.0090
 -12.500  -0.6596   0.02896   0.02240  -0.1077   0.6786   0.0091
 -12.250  -0.6505   0.02795   0.02128  -0.1063   0.6752   0.0092
 -12.000  -0.6414   0.02692   0.02015  -0.1048   0.6719   0.0093
 -11.500  -0.6201   0.02506   0.01809  -0.1018   0.6663   0.0096
 -11.250  -0.6083   0.02417   0.01711  -0.1003   0.6635   0.0097
 -11.000  -0.5958   0.02333   0.01618  -0.0988   0.6609   0.0098
 -10.750  -0.5822   0.02258   0.01535  -0.0974   0.6583   0.0100
 -10.500  -0.5674   0.02195   0.01462  -0.0960   0.6560   0.0102
 -10.250  -0.5529   0.02125   0.01383  -0.0945   0.6538   0.0104
 -10.000  -0.5375   0.02065   0.01313  -0.0931   0.6517   0.0106
  -9.750  -0.5215   0.02007   0.01248  -0.0917   0.6500   0.0107
  -9.500  -0.5068   0.01940   0.01176  -0.0902   0.6483   0.0110
  -9.250  -0.4920   0.01875   0.01108  -0.0886   0.6464   0.0112
  -9.000  -0.4760   0.01820   0.01050  -0.0870   0.6446   0.0116
  -8.750  -0.4594   0.01770   0.00996  -0.0855   0.6428   0.0118
  -8.500  -0.4426   0.01724   0.00945  -0.0840   0.6411   0.0121
  -8.250  -0.4258   0.01681   0.00897  -0.0824   0.6395   0.0124
  -8.000  -0.4092   0.01644   0.00854  -0.0807   0.6379   0.0128
  -7.750  -0.3923   0.01610   0.00814  -0.0790   0.6364   0.0130
  -7.500  -0.3744   0.01579   0.00777  -0.0775   0.6349   0.0134
  -7.250  -0.3559   0.01540   0.00735  -0.0760   0.6335   0.0140
  -7.000  -0.3356   0.01507   0.00701  -0.0750   0.6321   0.0146
  -6.750  -0.3146   0.01477   0.00668  -0.0739   0.6306   0.0153
  -6.500  -0.2930   0.01449   0.00637  -0.0730   0.6293   0.0162
  -6.250  -0.2717   0.01419   0.00606  -0.0721   0.6280   0.0175
  -6.000  -0.2496   0.01393   0.00579  -0.0712   0.6267   0.0191
  -5.750  -0.2278   0.01365   0.00551  -0.0703   0.6254   0.0221
  -5.500  -0.2056   0.01339   0.00525  -0.0695   0.6242   0.0265
  -5.250  -0.1833   0.01313   0.00501  -0.0687   0.6230   0.0333
  -5.000  -0.1609   0.01288   0.00479  -0.0679   0.6219   0.0434
  -4.750  -0.1384   0.01263   0.00459  -0.0672   0.6208   0.0570
  -4.500  -0.1156   0.01239   0.00441  -0.0665   0.6197   0.0724
  -4.250  -0.0926   0.01216   0.00424  -0.0658   0.6186   0.0925
  -3.750  -0.0471   0.01165   0.00393  -0.0645   0.6166   0.1468
  -3.500  -0.0270   0.01122   0.00376  -0.0634   0.6157   0.2046
  -3.250  -0.0081   0.01071   0.00357  -0.0622   0.6146   0.2825
  -3.000   0.0107   0.01020   0.00338  -0.0609   0.6133   0.3655
  -2.750   0.0288   0.00965   0.00318  -0.0595   0.6122   0.4601
  -2.500   0.0459   0.00904   0.00301  -0.0577   0.6112   0.5702
  -2.250   0.0671   0.00878   0.00310  -0.0565   0.6102   0.6601
  -2.000   0.0940   0.00882   0.00318  -0.0563   0.6092   0.6951
  -1.750   0.1219   0.00888   0.00323  -0.0563   0.6082   0.7129
  -1.500   0.1500   0.00895   0.00327  -0.0564   0.6072   0.7254
  -1.250   0.1782   0.00903   0.00333  -0.0565   0.6063   0.7346
  -1.000   0.2065   0.00911   0.00335  -0.0567   0.6053   0.7447
  -0.750   0.2345   0.00923   0.00349  -0.0567   0.6044   0.7545
  -0.500   0.2625   0.00935   0.00357  -0.0568   0.6033   0.7637
  -0.250   0.2908   0.00948   0.00370  -0.0568   0.6022   0.7704
   0.000   0.3193   0.00960   0.00377  -0.0571   0.6012   0.7758
   0.250   0.3479   0.00966   0.00380  -0.0575   0.6004   0.7790
   0.500   0.3762   0.00969   0.00383  -0.0577   0.5996   0.7809
   0.750   0.4045   0.00972   0.00388  -0.0580   0.5986   0.7827
   1.000   0.4327   0.00976   0.00393  -0.0582   0.5974   0.7845
   1.250   0.4610   0.00981   0.00398  -0.0585   0.5962   0.7862
   1.500   0.4893   0.00985   0.00403  -0.0588   0.5950   0.7880
   1.750   0.5176   0.00989   0.00407  -0.0591   0.5937   0.7897
   2.000   0.5458   0.00993   0.00411  -0.0594   0.5922   0.7914
   2.250   0.5742   0.00996   0.00413  -0.0597   0.5907   0.7928
   2.500   0.6025   0.00999   0.00415  -0.0601   0.5891   0.7943
   2.750   0.6309   0.01003   0.00417  -0.0604   0.5874   0.7958
   3.000   0.6596   0.01008   0.00420  -0.0608   0.5857   0.7970
   3.250   0.6878   0.01013   0.00426  -0.0611   0.5839   0.7981
   3.500   0.7144   0.01015   0.00434  -0.0611   0.5818   0.7992
   3.750   0.7412   0.01016   0.00440  -0.0611   0.5790   0.8004
   4.000   0.7682   0.01018   0.00445  -0.0612   0.5761   0.8018
   4.250   0.7953   0.01018   0.00448  -0.0612   0.5733   0.8033
   4.500   0.8227   0.01019   0.00449  -0.0614   0.5703   0.8046
   4.750   0.8493   0.01022   0.00454  -0.0614   0.5669   0.8060
   5.000   0.8748   0.01023   0.00462  -0.0612   0.5627   0.8074
   5.250   0.9006   0.01024   0.00466  -0.0610   0.5583   0.8088
   5.500   0.9268   0.01025   0.00467  -0.0609   0.5542   0.8102
   5.750   0.9524   0.01029   0.00476  -0.0607   0.5498   0.8116
   6.000   0.9773   0.01032   0.00486  -0.0604   0.5439   0.8131
   6.250   1.0018   0.01035   0.00489  -0.0600   0.5382   0.8146
   6.500   1.0255   0.01039   0.00501  -0.0595   0.5306   0.8162
   6.750   1.0477   0.01043   0.00507  -0.0586   0.5215   0.8178
   7.000   1.0689   0.01050   0.00518  -0.0576   0.5090   0.8194
   7.250   1.0862   0.01063   0.00528  -0.0558   0.4903   0.8213
   7.500   1.0942   0.01091   0.00546  -0.0523   0.4633   0.8236
   7.750   1.0915   0.01140   0.00582  -0.0468   0.4344   0.8264
   8.000   1.0889   0.01209   0.00639  -0.0416   0.4079   0.8293
   8.250   1.0851   0.01289   0.00709  -0.0366   0.3843   0.8322
   8.500   1.0810   0.01378   0.00793  -0.0319   0.3613   0.8354
   8.750   1.0736   0.01494   0.00903  -0.0271   0.3384   0.8394
   9.000   1.0689   0.01621   0.01024  -0.0232   0.3185   0.8436
   9.250   1.0659   0.01759   0.01156  -0.0198   0.2995   0.8474
   9.500   1.0633   0.01904   0.01299  -0.0167   0.2817   0.8513
   9.750   1.0596   0.02064   0.01455  -0.0138   0.2626   0.8558
  10.000   1.0601   0.02211   0.01599  -0.0114   0.2474   0.8607
  10.500   1.0606   0.02518   0.01901  -0.0069   0.2160   0.8715
  10.750   1.0641   0.02656   0.02038  -0.0051   0.2034   0.8782
  11.000   1.0668   0.02801   0.02182  -0.0032   0.1899   0.8860
  11.250   1.0711   0.02939   0.02321  -0.0016   0.1787   0.8965
  11.500   1.0763   0.03081   0.02465  -0.0002   0.1668   0.9120
  11.750   1.0909   0.03233   0.02622  -0.0010   0.1540   0.9342
  12.000   1.1160   0.03406   0.02795  -0.0042   0.1406   0.9636
  12.500   1.1300   0.03697   0.03081  -0.0023   0.1227   1.0000
  12.750   1.1388   0.03838   0.03221  -0.0016   0.1147   1.0000
  13.000   1.1468   0.03990   0.03371  -0.0009   0.1073   1.0000
  13.250   1.1549   0.04142   0.03522  -0.0003   0.1005   1.0000
  13.500   1.1639   0.04288   0.03668   0.0003   0.0941   1.0000
  13.750   1.1711   0.04453   0.03832   0.0009   0.0882   1.0000
  14.000   1.1805   0.04602   0.03982   0.0013   0.0827   1.0000
  14.250   1.1875   0.04772   0.04152   0.0018   0.0772   1.0000
  14.500   1.1952   0.04941   0.04321   0.0022   0.0711   1.0000
  14.750   1.2016   0.05122   0.04501   0.0027   0.0658   1.0000
  15.000   1.2100   0.05289   0.04670   0.0029   0.0616   1.0000
  15.250   1.2156   0.05485   0.04865   0.0033   0.0573   1.0000
  15.500   1.2244   0.05653   0.05037   0.0035   0.0541   1.0000
  15.750   1.2315   0.05841   0.05228   0.0036   0.0513   1.0000
  16.000   1.2377   0.06041   0.05430   0.0038   0.0488   1.0000
  16.250   1.2459   0.06222   0.05617   0.0038   0.0467   1.0000
  16.500   1.2518   0.06430   0.05830   0.0039   0.0444   1.0000
  16.750   1.2568   0.06651   0.06053   0.0039   0.0422   1.0000
  17.000   1.2639   0.06854   0.06262   0.0038   0.0403   1.0000
  17.250   1.2692   0.07080   0.06494   0.0036   0.0386   1.0000
  17.500   1.2732   0.07320   0.06737   0.0034   0.0365   1.0000
  17.750   1.2776   0.07561   0.06985   0.0031   0.0347   1.0000
  18.000   1.2824   0.07801   0.07231   0.0028   0.0330   1.0000
  18.250   1.2848   0.08075   0.07510   0.0024   0.0314   1.0000
  18.500   1.2880   0.08342   0.07783   0.0019   0.0298   1.0000
  18.750   1.2910   0.08616   0.08064   0.0013   0.0285   1.0000
  19.000   1.2928   0.08907   0.08361   0.0007   0.0270   1.0000
  19.250   1.2930   0.09224   0.08684  -0.0001   0.0256   1.0000
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