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RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAF 6 AIRFOIL (raf6-il)
Reynolds number: 100,000
Max Cl/Cd: 52.48 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf6-il-100000-n5.txt
Download as CSV file: xf-raf6-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 6 AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3544   0.11033   0.10587  -0.0274   1.0000   0.0365
  -8.000  -0.3671   0.10897   0.10461  -0.0256   1.0000   0.0366
  -7.750  -0.3767   0.10724   0.10295  -0.0253   0.9989   0.0367
  -7.500  -0.3586   0.10275   0.09845  -0.0339   0.9930   0.0369
  -7.250  -0.3380   0.09801   0.09367  -0.0419   0.9873   0.0370
  -7.000  -0.3196   0.09356   0.08915  -0.0481   0.9814   0.0371
  -6.750  -0.3007   0.08844   0.08400  -0.0533   0.9770   0.0374
  -6.500  -0.2983   0.08360   0.07928  -0.0486   0.9745   0.0387
  -6.250  -0.2838   0.08001   0.07569  -0.0496   0.9706   0.0402
  -6.000  -0.2665   0.07625   0.07189  -0.0530   0.9653   0.0420
  -5.750  -0.2451   0.07216   0.06773  -0.0577   0.9601   0.0441
  -5.500  -0.2239   0.06818   0.06364  -0.0621   0.9540   0.0462
  -5.000  -0.1596   0.06134   0.05596  -0.0738   0.9416   0.0497
  -4.750  -0.1432   0.05574   0.05052  -0.0750   0.9383   0.0508
  -4.500  -0.1180   0.05200   0.04673  -0.0771   0.9357   0.0521
  -4.000  -0.0631   0.04459   0.03870  -0.0794   0.9256   0.0351
  -3.750  -0.0303   0.04117   0.03499  -0.0818   0.9231   0.0342
  -3.500  -0.0077   0.03857   0.03211  -0.0816   0.9170   0.0333
  -3.250   0.0235   0.03569   0.02887  -0.0827   0.9132   0.0316
  -3.000   0.0592   0.03293   0.02565  -0.0841   0.9106   0.0304
  -2.750   0.0953   0.03058   0.02284  -0.0855   0.9078   0.0301
  -2.500   0.1215   0.02906   0.02098  -0.0849   0.9003   0.0319
  -2.250   0.1612   0.02712   0.01860  -0.0865   0.8961   0.0332
  -2.000   0.1957   0.02547   0.01659  -0.0870   0.8894   0.0340
  -1.750   0.2316   0.02425   0.01502  -0.0877   0.8824   0.0368
  -1.500   0.2722   0.02250   0.01317  -0.0896   0.8789   0.0395
  -1.250   0.2987   0.02172   0.01236  -0.0891   0.8705   0.0436
  -1.000   0.3362   0.02064   0.01117  -0.0903   0.8649   0.0489
  -0.750   0.3695   0.01958   0.01012  -0.0908   0.8553   0.0573
  -0.500   0.4140   0.01842   0.00883  -0.0932   0.8466   0.0712
  -0.250   0.4454   0.01771   0.00811  -0.0933   0.8343   0.0968
   0.000   0.4887   0.01501   0.00772  -0.0956   0.8277   1.0000
   0.250   0.5205   0.01489   0.00734  -0.0960   0.8168   1.0000
   0.500   0.5508   0.01482   0.00707  -0.0961   0.8047   1.0000
   0.750   0.5831   0.01471   0.00679  -0.0967   0.7920   1.0000
   1.000   0.6136   0.01465   0.00657  -0.0968   0.7772   1.0000
   1.250   0.6409   0.01465   0.00645  -0.0964   0.7599   1.0000
   1.500   0.6667   0.01466   0.00635  -0.0957   0.7400   1.0000
   1.750   0.6932   0.01466   0.00623  -0.0951   0.7161   1.0000
   2.000   0.7190   0.01468   0.00612  -0.0943   0.6849   1.0000
   2.250   0.7471   0.01471   0.00594  -0.0940   0.6437   1.0000
   2.500   0.7757   0.01486   0.00575  -0.0937   0.5915   1.0000
   2.750   0.7993   0.01523   0.00573  -0.0926   0.5359   1.0000
   3.000   0.8195   0.01575   0.00588  -0.0910   0.4888   1.0000
   3.250   0.8392   0.01629   0.00614  -0.0895   0.4521   1.0000
   3.500   0.8594   0.01682   0.00644  -0.0881   0.4231   1.0000
   3.750   0.8801   0.01732   0.00677  -0.0868   0.3988   1.0000
   4.000   0.9009   0.01782   0.00713  -0.0856   0.3775   1.0000
   4.250   0.9222   0.01829   0.00749  -0.0845   0.3581   1.0000
   4.500   0.9436   0.01876   0.00786  -0.0835   0.3413   1.0000
   4.750   0.9649   0.01925   0.00827  -0.0824   0.3273   1.0000
   5.000   0.9867   0.01972   0.00868  -0.0815   0.3152   1.0000
   5.250   1.0087   0.02019   0.00912  -0.0806   0.3042   1.0000
   5.500   1.0301   0.02071   0.00958  -0.0796   0.2948   1.0000
   5.750   1.0521   0.02119   0.01006  -0.0788   0.2858   1.0000
   6.000   1.0739   0.02173   0.01058  -0.0779   0.2785   1.0000
   6.250   1.0962   0.02223   0.01112  -0.0772   0.2712   1.0000
   6.500   1.1176   0.02282   0.01166  -0.0763   0.2649   1.0000
   6.750   1.1399   0.02333   0.01228  -0.0755   0.2579   1.0000
   7.000   1.1613   0.02392   0.01287  -0.0747   0.2521   1.0000
   7.250   1.1835   0.02450   0.01352  -0.0740   0.2463   1.0000
   7.500   1.2050   0.02508   0.01420  -0.0731   0.2405   1.0000
   8.000   1.2479   0.02635   0.01563  -0.0715   0.2301   1.0000
   8.250   1.2688   0.02699   0.01638  -0.0707   0.2250   1.0000
   8.500   1.2905   0.02773   0.01713  -0.0700   0.2207   1.0000
   8.750   1.3104   0.02839   0.01803  -0.0690   0.2156   1.0000
   9.000   1.3304   0.02910   0.01889  -0.0680   0.2109   1.0000
   9.250   1.3512   0.02985   0.01973  -0.0672   0.2071   1.0000
   9.500   1.3713   0.03067   0.02074  -0.0663   0.2031   1.0000
   9.750   1.3862   0.03136   0.02169  -0.0644   0.1976   1.0000
  10.000   1.3947   0.03186   0.02223  -0.0616   0.1905   1.0000
  10.250   1.3984   0.03236   0.02298  -0.0581   0.1808   1.0000
  10.500   1.4029   0.03294   0.02366  -0.0550   0.1718   1.0000
  10.750   1.4096   0.03361   0.02455  -0.0523   0.1620   1.0000
  11.000   1.4162   0.03439   0.02548  -0.0499   0.1491   1.0000
  11.250   1.4229   0.03534   0.02653  -0.0477   0.1340   1.0000
  11.500   1.4295   0.03657   0.02781  -0.0456   0.1112   1.0000
  11.750   1.4275   0.03865   0.02970  -0.0430   0.0772   1.0000
  12.000   1.4064   0.04267   0.03328  -0.0395   0.0337   1.0000
  12.250   1.3962   0.04593   0.03662  -0.0370   0.0287   1.0000
  12.500   1.3864   0.04930   0.04017  -0.0350   0.0255   1.0000
  12.750   1.3772   0.05276   0.04384  -0.0334   0.0235   1.0000
  13.000   1.3679   0.05639   0.04774  -0.0324   0.0223   1.0000
  13.250   1.3557   0.06060   0.05220  -0.0320   0.0215   1.0000
  13.500   1.3406   0.06550   0.05736  -0.0322   0.0210   1.0000
  13.750   1.3230   0.07120   0.06331  -0.0333   0.0207   1.0000
  14.000   1.3031   0.07787   0.07023  -0.0355   0.0206   1.0000
  14.250   1.2807   0.08556   0.07815  -0.0386   0.0208   1.0000
  14.500   1.2570   0.09402   0.08684  -0.0424   0.0210   1.0000
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