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

RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il)
Reynolds number: 500,000
Max Cl/Cd: 58.29 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-bqm34-il-500000-n5.txt
Download as CSV file: xf-bqm34-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RYAN BQM-34 FIREBEE 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
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.9610   0.11149   0.10866   0.0030   1.0000   0.0092
 -16.000  -1.0127   0.09577   0.09271  -0.0059   1.0000   0.0091
 -15.750  -1.0459   0.08454   0.08128  -0.0126   1.0000   0.0090
 -15.500  -1.0740   0.07481   0.07137  -0.0186   1.0000   0.0089
 -15.250  -1.0940   0.06702   0.06340  -0.0235   1.0000   0.0089
 -15.000  -1.1117   0.06012   0.05633  -0.0279   1.0000   0.0089
 -14.750  -1.1291   0.05384   0.04990  -0.0316   1.0000   0.0090
 -14.500  -1.1404   0.04893   0.04483  -0.0342   1.0000   0.0090
 -14.250  -1.1503   0.04466   0.04041  -0.0359   1.0000   0.0090
 -14.000  -1.1561   0.04127   0.03688  -0.0369   1.0000   0.0092
 -13.750  -1.1623   0.03814   0.03361  -0.0371   1.0000   0.0092
 -13.500  -1.1640   0.03575   0.03109  -0.0368   1.0000   0.0093
 -13.250  -1.1652   0.03361   0.02882  -0.0358   1.0000   0.0094
 -13.000  -1.1615   0.03211   0.02722  -0.0346   1.0000   0.0096
 -12.750  -1.1596   0.03054   0.02553  -0.0327   1.0000   0.0097
 -12.500  -1.1577   0.02906   0.02392  -0.0304   1.0000   0.0098
 -12.250  -1.1521   0.02795   0.02271  -0.0280   1.0000   0.0100
 -12.000  -1.1467   0.02680   0.02144  -0.0253   1.0000   0.0101
 -11.750  -1.1359   0.02578   0.02030  -0.0234   1.0000   0.0103
 -11.500  -1.1234   0.02475   0.01916  -0.0217   1.0000   0.0106
 -11.250  -1.1094   0.02378   0.01806  -0.0201   1.0000   0.0108
 -11.000  -1.0944   0.02282   0.01698  -0.0185   1.0000   0.0111
 -10.750  -1.0778   0.02196   0.01601  -0.0171   1.0000   0.0113
 -10.500  -1.0606   0.02113   0.01507  -0.0158   1.0000   0.0116
 -10.250  -1.0444   0.02016   0.01403  -0.0143   1.0000   0.0120
 -10.000  -1.0254   0.01947   0.01327  -0.0132   1.0000   0.0125
  -9.750  -1.0056   0.01884   0.01258  -0.0121   1.0000   0.0130
  -9.500  -0.9853   0.01824   0.01192  -0.0110   1.0000   0.0136
  -9.250  -0.9646   0.01766   0.01127  -0.0100   1.0000   0.0142
  -9.000  -0.9437   0.01711   0.01063  -0.0089   1.0000   0.0148
  -8.750  -0.9239   0.01642   0.00989  -0.0077   1.0000   0.0155
  -8.500  -0.9029   0.01589   0.00932  -0.0067   1.0000   0.0163
  -8.250  -0.8813   0.01541   0.00881  -0.0056   1.0000   0.0172
  -8.000  -0.8596   0.01496   0.00830  -0.0046   1.0000   0.0182
  -7.750  -0.8379   0.01452   0.00779  -0.0035   1.0000   0.0191
  -7.500  -0.8168   0.01402   0.00729  -0.0024   1.0000   0.0206
  -7.250  -0.7948   0.01365   0.00690  -0.0014   1.0000   0.0222
  -7.000  -0.7724   0.01331   0.00651  -0.0004   1.0000   0.0237
  -6.750  -0.7509   0.01288   0.00608   0.0007   1.0000   0.0259
  -6.500  -0.7289   0.01254   0.00573   0.0018   1.0000   0.0281
  -6.250  -0.7067   0.01224   0.00540   0.0029   1.0000   0.0302
  -6.000  -0.6852   0.01188   0.00506   0.0041   1.0000   0.0337
  -5.750  -0.6600   0.01159   0.00475   0.0045   0.9991   0.0370
  -5.500  -0.6268   0.01123   0.00442   0.0031   0.9949   0.0428
  -5.250  -0.5948   0.01091   0.00412   0.0020   0.9897   0.0492
  -5.000  -0.5615   0.01061   0.00383   0.0007   0.9846   0.0572
  -4.750  -0.5300   0.01029   0.00356  -0.0002   0.9781   0.0685
  -4.500  -0.4961   0.00995   0.00330  -0.0016   0.9722   0.0843
  -4.250  -0.4638   0.00962   0.00305  -0.0027   0.9642   0.1046
  -4.000  -0.4295   0.00928   0.00282  -0.0043   0.9561   0.1296
  -3.750  -0.3973   0.00894   0.00260  -0.0054   0.9445   0.1604
  -3.500  -0.3654   0.00859   0.00238  -0.0064   0.9312   0.1973
  -3.250  -0.3353   0.00824   0.00218  -0.0069   0.9153   0.2406
  -3.000  -0.3078   0.00791   0.00200  -0.0069   0.8976   0.2893
  -2.500  -0.2571   0.00731   0.00169  -0.0059   0.8610   0.3964
  -2.250  -0.2323   0.00708   0.00159  -0.0052   0.8434   0.4465
  -2.000  -0.2073   0.00690   0.00151  -0.0045   0.8267   0.4910
  -1.750  -0.1820   0.00677   0.00144  -0.0039   0.8107   0.5287
  -1.500  -0.1564   0.00667   0.00139  -0.0033   0.7953   0.5610
  -1.250  -0.1305   0.00660   0.00135  -0.0027   0.7802   0.5893
  -1.000  -0.1045   0.00654   0.00132  -0.0021   0.7652   0.6145
  -0.750  -0.0784   0.00650   0.00130  -0.0016   0.7501   0.6367
  -0.500  -0.0522   0.00648   0.00129  -0.0011   0.7343   0.6581
  -0.250  -0.0260   0.00646   0.00128  -0.0006   0.7175   0.6792
   0.000   0.0000   0.00645   0.00128   0.0000   0.6991   0.6991
   0.250   0.0260   0.00646   0.00128   0.0006   0.6790   0.7175
   0.500   0.0522   0.00648   0.00129   0.0011   0.6579   0.7344
   0.750   0.0784   0.00650   0.00130   0.0016   0.6366   0.7502
   1.000   0.1045   0.00654   0.00132   0.0022   0.6144   0.7653
   1.250   0.1306   0.00659   0.00135   0.0027   0.5897   0.7802
   1.500   0.1564   0.00667   0.00139   0.0033   0.5609   0.7953
   1.750   0.1819   0.00677   0.00144   0.0039   0.5287   0.8108
   2.000   0.2073   0.00690   0.00151   0.0045   0.4909   0.8267
   2.250   0.2322   0.00709   0.00159   0.0052   0.4452   0.8434
   2.500   0.2570   0.00732   0.00169   0.0059   0.3946   0.8610
   3.000   0.3078   0.00791   0.00200   0.0069   0.2899   0.8975
   3.250   0.3353   0.00825   0.00218   0.0069   0.2401   0.9153
   3.500   0.3654   0.00859   0.00238   0.0064   0.1975   0.9314
   3.750   0.3973   0.00894   0.00260   0.0054   0.1602   0.9446
   4.000   0.4296   0.00928   0.00282   0.0043   0.1293   0.9562
   4.250   0.4638   0.00962   0.00305   0.0027   0.1045   0.9642
   4.500   0.4962   0.00995   0.00330   0.0016   0.0841   0.9723
   4.750   0.5299   0.01029   0.00356   0.0002   0.0688   0.9782
   5.000   0.5616   0.01061   0.00383  -0.0008   0.0574   0.9847
   5.250   0.5948   0.01091   0.00412  -0.0021   0.0492   0.9898
   5.500   0.6269   0.01122   0.00442  -0.0031   0.0428   0.9949
   5.750   0.6601   0.01159   0.00475  -0.0045   0.0370   0.9992
   6.000   0.6851   0.01188   0.00506  -0.0040   0.0338   1.0000
   6.250   0.7066   0.01224   0.00540  -0.0029   0.0302   1.0000
   6.500   0.7288   0.01254   0.00573  -0.0018   0.0280   1.0000
   6.750   0.7508   0.01288   0.00608  -0.0007   0.0258   1.0000
   7.000   0.7723   0.01331   0.00651   0.0004   0.0237   1.0000
   7.250   0.7947   0.01365   0.00690   0.0014   0.0222   1.0000
   7.500   0.8167   0.01402   0.00729   0.0024   0.0206   1.0000
   7.750   0.8379   0.01451   0.00779   0.0036   0.0191   1.0000
   8.000   0.8597   0.01495   0.00829   0.0046   0.0182   1.0000
   8.250   0.8813   0.01541   0.00880   0.0057   0.0172   1.0000
   8.500   0.9030   0.01587   0.00931   0.0066   0.0163   1.0000
   8.750   0.9239   0.01643   0.00990   0.0077   0.0155   1.0000
   9.000   0.9437   0.01712   0.01064   0.0089   0.0148   1.0000
   9.250   0.9647   0.01767   0.01127   0.0100   0.0142   1.0000
   9.500   0.9852   0.01826   0.01194   0.0110   0.0136   1.0000
   9.750   1.0055   0.01886   0.01261   0.0121   0.0130   1.0000
  10.000   1.0257   0.01946   0.01327   0.0131   0.0125   1.0000
  10.250   1.0447   0.02016   0.01403   0.0143   0.0120   1.0000
  10.500   1.0612   0.02109   0.01503   0.0157   0.0116   1.0000
  10.750   1.0780   0.02197   0.01602   0.0171   0.0113   1.0000
  11.000   1.0946   0.02282   0.01698   0.0185   0.0111   1.0000
  11.250   1.1097   0.02377   0.01805   0.0200   0.0109   1.0000
  11.500   1.1239   0.02474   0.01914   0.0216   0.0106   1.0000
  11.750   1.1364   0.02577   0.02029   0.0233   0.0103   1.0000
  12.000   1.1473   0.02680   0.02144   0.0252   0.0101   1.0000
  12.250   1.1529   0.02793   0.02269   0.0279   0.0099   1.0000
  12.500   1.1591   0.02900   0.02385   0.0302   0.0097   1.0000
  12.750   1.1618   0.03041   0.02538   0.0325   0.0096   1.0000
  13.000   1.1651   0.03185   0.02694   0.0343   0.0095   1.0000
  13.250   1.1666   0.03356   0.02876   0.0357   0.0093   1.0000
  13.500   1.1665   0.03556   0.03088   0.0366   0.0092   1.0000
  13.750   1.1613   0.03834   0.03382   0.0370   0.0092   1.0000
  14.000   1.1581   0.04113   0.03672   0.0367   0.0091   1.0000
  14.250   1.1510   0.04468   0.04043   0.0358   0.0090   1.0000
  14.500   1.1424   0.04881   0.04470   0.0340   0.0090   1.0000
  14.750   1.1294   0.05397   0.05004   0.0314   0.0090   1.0000
  15.000   1.1159   0.05968   0.05591   0.0280   0.0090   1.0000
  15.250   1.0964   0.06684   0.06321   0.0234   0.0089   1.0000
  15.500   1.0755   0.07483   0.07140   0.0184   0.0090   1.0000
  15.750   1.0508   0.08394   0.08068   0.0127   0.0090   1.0000
  16.000   1.0141   0.09578   0.09271   0.0057   0.0090   1.0000
  16.250   0.9702   0.10976   0.10690  -0.0023   0.0092   1.0000
<< Back to RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il)

Polar data table (+)

Polar graphs


<< Back to RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il)