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GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GIII BL145 AIRFOIL (giiif-il)
Reynolds number: 200,000
Max Cl/Cd: 61.65 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiif-il-200000.txt
Download as CSV file: xf-giiif-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GIII BL145 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5696   0.08859   0.08525  -0.0104   1.0000   0.0385
  -8.250  -0.5738   0.08336   0.08005  -0.0167   1.0000   0.0391
  -8.000  -0.5761   0.07853   0.07512  -0.0227   1.0000   0.0402
  -7.750  -0.5738   0.07461   0.07101  -0.0263   1.0000   0.0408
  -7.500  -0.5115   0.05733   0.05414  -0.0286   1.0000   0.0440
  -7.250  -0.5086   0.05367   0.05045  -0.0284   1.0000   0.0462
  -7.000  -0.5074   0.04936   0.04605  -0.0289   1.0000   0.0480
  -6.750  -0.5046   0.04500   0.04153  -0.0291   1.0000   0.0507
  -6.500  -0.5002   0.04292   0.03888  -0.0279   1.0000   0.0535
  -6.000  -0.5203   0.04560   0.04110  -0.0255   1.0000   0.0556
  -5.750  -0.5081   0.04281   0.03825  -0.0242   1.0000   0.0573
  -5.500  -0.4958   0.04030   0.03561  -0.0225   1.0000   0.0600
  -5.250  -0.4861   0.03903   0.03362  -0.0189   1.0000   0.0674
  -5.000  -0.4744   0.03050   0.02453  -0.0151   1.0000   0.0424
  -4.750  -0.4609   0.02701   0.02088  -0.0127   1.0000   0.0363
  -4.500  -0.4455   0.02373   0.01712  -0.0101   1.0000   0.0347
  -4.250  -0.4281   0.02228   0.01538  -0.0083   1.0000   0.0375
  -4.000  -0.4073   0.02008   0.01280  -0.0067   1.0000   0.0376
  -3.750  -0.3788   0.01821   0.01059  -0.0065   0.9988   0.0389
  -3.500  -0.3417   0.01642   0.00856  -0.0082   0.9957   0.0425
  -3.250  -0.3045   0.01544   0.00755  -0.0103   0.9915   0.0507
  -3.000  -0.2685   0.01424   0.00635  -0.0121   0.9870   0.0616
  -2.750  -0.2302   0.01342   0.00558  -0.0147   0.9830   0.0865
  -2.500  -0.1955   0.01276   0.00502  -0.0165   0.9766   0.1174
  -2.250  -0.1583   0.01200   0.00446  -0.0190   0.9716   0.1670
  -2.000  -0.1403   0.00945   0.00437  -0.0175   0.9665   0.7644
  -1.750  -0.1139   0.00946   0.00458  -0.0158   0.9599   0.8604
  -1.500  -0.0799   0.00963   0.00472  -0.0158   0.9559   0.9040
  -1.250  -0.0454   0.00982   0.00482  -0.0162   0.9502   0.9324
  -1.000  -0.0010   0.01000   0.00491  -0.0189   0.9471   0.9534
  -0.750   0.0557   0.01013   0.00494  -0.0244   0.9467   0.9685
  -0.500   0.1305   0.01013   0.00485  -0.0338   0.9509   0.9846
  -0.250   0.1787   0.00999   0.00466  -0.0383   0.9451   0.9908
   0.000   0.2172   0.00985   0.00449  -0.0408   0.9346   0.9948
   0.250   0.2545   0.00967   0.00428  -0.0428   0.9219   0.9990
   0.500   0.2785   0.00957   0.00415  -0.0422   0.9069   1.0000
   0.750   0.2990   0.00950   0.00405  -0.0408   0.8923   1.0000
   1.000   0.3202   0.00946   0.00399  -0.0396   0.8793   1.0000
   1.250   0.3424   0.00944   0.00398  -0.0386   0.8676   1.0000
   1.500   0.3648   0.00943   0.00395  -0.0376   0.8564   1.0000
   1.750   0.3872   0.00943   0.00396  -0.0366   0.8448   1.0000
   2.000   0.4097   0.00945   0.00400  -0.0356   0.8328   1.0000
   2.250   0.4323   0.00948   0.00406  -0.0346   0.8208   1.0000
   2.500   0.4549   0.00952   0.00416  -0.0336   0.8086   1.0000
   2.750   0.4775   0.00955   0.00422  -0.0324   0.7951   1.0000
   3.000   0.4979   0.00946   0.00409  -0.0303   0.7719   1.0000
   3.250   0.5179   0.00935   0.00394  -0.0281   0.7399   1.0000
   3.500   0.5396   0.00932   0.00393  -0.0264   0.7095   1.0000
   3.750   0.5617   0.00934   0.00393  -0.0250   0.6763   1.0000
   4.000   0.5826   0.00945   0.00392  -0.0232   0.6232   1.0000
   4.250   0.6009   0.00983   0.00396  -0.0210   0.5190   1.0000
   4.500   0.6104   0.01127   0.00435  -0.0179   0.3180   1.0000
   4.750   0.6167   0.01375   0.00547  -0.0151   0.0867   1.0000
   5.000   0.6347   0.01492   0.00656  -0.0135   0.0606   1.0000
   5.250   0.6522   0.01622   0.00783  -0.0118   0.0501   1.0000
   5.500   0.6735   0.01715   0.00885  -0.0105   0.0454   1.0000
   5.750   0.6943   0.01826   0.00994  -0.0093   0.0402   1.0000
   6.000   0.7152   0.02010   0.01182  -0.0081   0.0368   1.0000
   6.250   0.7393   0.02161   0.01349  -0.0071   0.0349   1.0000
   6.500   0.7637   0.02357   0.01570  -0.0061   0.0336   1.0000
   6.750   0.7868   0.02507   0.01737  -0.0053   0.0308   1.0000
   7.000   0.8084   0.02703   0.01949  -0.0045   0.0287   1.0000
   7.250   0.8297   0.02995   0.02279  -0.0031   0.0288   1.0000
   7.500   0.8451   0.03564   0.02937   0.0000   0.0336   1.0000
  11.250   0.7555   0.11996   0.11651  -0.0199   0.0462   1.0000
  11.500   0.7530   0.12525   0.12178  -0.0227   0.0442   1.0000
  11.750   0.7543   0.12937   0.12588  -0.0243   0.0418   1.0000
  12.000   0.7614   0.13182   0.12835  -0.0234   0.0398   1.0000
  12.250   0.7648   0.13561   0.13216  -0.0202   0.0381   1.0000
  12.500   0.6029   0.13213   0.12880  -0.0100   0.0490   1.0000
  12.750   0.5923   0.13635   0.13300  -0.0132   0.0474   1.0000
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