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RAF 89 AIRFOIL (raf89-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAF 89 AIRFOIL (raf89-il)
Reynolds number: 100,000
Max Cl/Cd: 27.35 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf89-il-100000-n5.txt
Download as CSV file: xf-raf89-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 89 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
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -0.5522   0.12589   0.11872  -0.0631   1.0000   0.1134
 -17.500  -0.6506   0.10362   0.09619  -0.0720   1.0000   0.1246
 -17.250  -0.6214   0.10530   0.09798  -0.0708   1.0000   0.1259
 -17.000  -0.6029   0.10535   0.09810  -0.0703   1.0000   0.1276
 -16.750  -0.7041   0.08747   0.07982  -0.0773   1.0000   0.1355
 -16.500  -0.6830   0.08787   0.08035  -0.0764   1.0000   0.1376
 -16.250  -0.6808   0.08564   0.07815  -0.0767   1.0000   0.1408
 -16.000  -0.7225   0.07750   0.06980  -0.0792   1.0000   0.1458
 -15.750  -0.7264   0.07469   0.06701  -0.0794   1.0000   0.1490
 -15.500  -0.7256   0.07263   0.06500  -0.0793   1.0000   0.1525
 -15.250  -0.7460   0.06808   0.06036  -0.0799   1.0000   0.1568
 -15.000  -0.7634   0.06421   0.05642  -0.0800   1.0000   0.1608
 -14.750  -0.7630   0.06267   0.05496  -0.0791   1.0000   0.1641
 -14.500  -0.7766   0.05990   0.05218  -0.0782   1.0000   0.1680
 -14.250  -0.8015   0.05666   0.04885  -0.0767   1.0000   0.1719
 -13.750  -0.7734   0.05170   0.04388  -0.0818   0.9810   0.1822
 -13.500  -0.7679   0.04861   0.04065  -0.0845   0.9695   0.1880
 -13.250  -0.7481   0.04696   0.03903  -0.0868   0.9604   0.1931
 -13.000  -0.7417   0.04433   0.03625  -0.0889   0.9490   0.1993
 -12.750  -0.7207   0.04261   0.03451  -0.0916   0.9419   0.2050
 -12.500  -0.7056   0.04082   0.03265  -0.0935   0.9312   0.2110
 -12.250  -0.6871   0.03870   0.03038  -0.0966   0.9243   0.2178
 -12.000  -0.6646   0.03758   0.02927  -0.0985   0.9146   0.2236
 -11.750  -0.6485   0.03574   0.02724  -0.1007   0.9061   0.2306
 -11.500  -0.6251   0.03476   0.02625  -0.1024   0.8979   0.2364
 -11.250  -0.6077   0.03367   0.02509  -0.1033   0.8884   0.2426
 -11.000  -0.5914   0.03227   0.02348  -0.1047   0.8808   0.2493
 -10.750  -0.5740   0.03179   0.02304  -0.1042   0.8706   0.2544
 -10.500  -0.5590   0.03090   0.02204  -0.1042   0.8623   0.2608
 -10.250  -0.5472   0.02999   0.02098  -0.1037   0.8547   0.2666
 -10.000  -0.5305   0.02965   0.02068  -0.1028   0.8468   0.2714
  -9.750  -0.5171   0.02906   0.02001  -0.1018   0.8396   0.2772
  -9.500  -0.5088   0.02826   0.01900  -0.1003   0.8333   0.2832
  -9.250  -0.4926   0.02805   0.01888  -0.0988   0.8258   0.2877
  -9.000  -0.4795   0.02769   0.01849  -0.0971   0.8191   0.2930
  -8.750  -0.4694   0.02718   0.01785  -0.0951   0.8136   0.2989
  -8.500  -0.4549   0.02679   0.01742  -0.0935   0.8085   0.3043
  -8.250  -0.4442   0.02662   0.01729  -0.0910   0.8018   0.3090
  -8.000  -0.4348   0.02632   0.01695  -0.0884   0.7956   0.3146
  -7.750  -0.4275   0.02593   0.01642  -0.0855   0.7904   0.3204
  -7.500  -0.4025   0.02565   0.01616  -0.0852   0.7868   0.3258
  -7.250  -0.3974   0.02560   0.01615  -0.0816   0.7804   0.3306
  -7.000  -0.3924   0.02548   0.01598  -0.0779   0.7742   0.3362
  -6.750  -0.3843   0.02527   0.01568  -0.0747   0.7691   0.3419
  -6.500  -0.3582   0.02502   0.01548  -0.0745   0.7653   0.3475
  -6.250  -0.3441   0.02488   0.01531  -0.0723   0.7608   0.3536
  -6.000  -0.3422   0.02488   0.01528  -0.0680   0.7540   0.3593
  -5.750  -0.3268   0.02472   0.01514  -0.0659   0.7486   0.3652
  -5.500  -0.3052   0.02450   0.01494  -0.0649   0.7441   0.3715
  -5.250  -0.2837   0.02422   0.01457  -0.0638   0.7401   0.3791
  -5.000  -0.2766   0.02421   0.01458  -0.0603   0.7338   0.3852
  -4.750  -0.2635   0.02416   0.01462  -0.0577   0.7274   0.3914
  -4.500  -0.2464   0.02397   0.01440  -0.0558   0.7222   0.3991
  -4.250  -0.2227   0.02370   0.01410  -0.0550   0.7183   0.4072
  -4.000  -0.2017   0.02356   0.01400  -0.0538   0.7139   0.4150
  -3.750  -0.2006   0.02367   0.01415  -0.0491   0.7064   0.4225
  -3.500  -0.1842   0.02358   0.01412  -0.0471   0.7010   0.4305
  -3.250  -0.1615   0.02338   0.01394  -0.0460   0.6967   0.4400
  -3.000  -0.1333   0.02313   0.01369  -0.0459   0.6932   0.4504
  -2.750  -0.1342   0.02337   0.01405  -0.0408   0.6855   0.4587
  -2.500  -0.1225   0.02339   0.01410  -0.0378   0.6793   0.4687
  -2.250  -0.0995   0.02328   0.01403  -0.0367   0.6747   0.4801
  -2.000  -0.0698   0.02310   0.01385  -0.0367   0.6711   0.4922
  -1.750  -0.0718   0.02336   0.01417  -0.0314   0.6633   0.5029
  -1.500  -0.0597   0.02346   0.01431  -0.0285   0.6568   0.5135
  -1.250  -0.0359   0.02331   0.01412  -0.0275   0.6521   0.5270
  -1.000  -0.0041   0.02312   0.01387  -0.0278   0.6486   0.5403
  -0.750  -0.0152   0.02351   0.01435  -0.0210   0.6392   0.5489
  -0.500   0.0011   0.02347   0.01427  -0.0187   0.6332   0.5607
  -0.250   0.0330   0.02326   0.01403  -0.0190   0.6291   0.5715
   0.000   0.0354   0.02343   0.01420  -0.0145   0.6217   0.5816
   0.250   0.0419   0.02352   0.01432  -0.0106   0.6141   0.5904
   0.500   0.0721   0.02331   0.01408  -0.0106   0.6094   0.6006
   0.750   0.0900   0.02324   0.01397  -0.0086   0.6037   0.6103
   1.000   0.0815   0.02350   0.01432  -0.0022   0.5944   0.6171
   1.250   0.1092   0.02327   0.01403  -0.0019   0.5894   0.6272
   1.500   0.1317   0.02317   0.01394  -0.0006   0.5836   0.6352
   1.750   0.1230   0.02351   0.01435   0.0056   0.5741   0.6423
   2.000   0.1514   0.02325   0.01401   0.0058   0.5690   0.6519
   2.250   0.1659   0.02336   0.01417   0.0082   0.5621   0.6586
   2.500   0.1704   0.02366   0.01451   0.0121   0.5535   0.6661
   2.750   0.2013   0.02334   0.01411   0.0120   0.5485   0.6753
   3.000   0.2059   0.02375   0.01461   0.0157   0.5400   0.6816
   3.250   0.2220   0.02387   0.01473   0.0177   0.5327   0.6893
   3.750   0.2539   0.02416   0.01504   0.0215   0.5186   0.7045
   4.000   0.2764   0.02415   0.01502   0.0225   0.5120   0.7126
   4.250   0.3131   0.02378   0.01456   0.0215   0.5073   0.7214
   4.500   0.3075   0.02460   0.01550   0.0261   0.4977   0.7284
   4.750   0.3336   0.02452   0.01538   0.0266   0.4915   0.7374
   5.000   0.3593   0.02451   0.01535   0.0270   0.4856   0.7460
   5.250   0.3647   0.02512   0.01604   0.0299   0.4773   0.7556
   5.500   0.3922   0.02504   0.01593   0.0301   0.4716   0.7677
   5.750   0.4160   0.02520   0.01613   0.0306   0.4653   0.7802
   6.000   0.4264   0.02578   0.01678   0.0326   0.4576   0.7929
   6.250   0.4592   0.02571   0.01670   0.0319   0.4518   0.8044
   6.500   0.4852   0.02596   0.01697   0.0317   0.4457   0.8158
   6.750   0.4997   0.02662   0.01772   0.0327   0.4383   0.8293
   7.000   0.5373   0.02664   0.01775   0.0308   0.4323   0.8414
   7.500   0.5973   0.02781   0.01907   0.0277   0.4187   0.8720
   7.750   0.6448   0.02799   0.01924   0.0239   0.4127   0.8865
   8.000   0.6872   0.02853   0.01981   0.0203   0.4064   0.9027
   8.250   0.7211   0.02956   0.02094   0.0172   0.3987   0.9196
   8.500   0.7696   0.02984   0.02119   0.0131   0.3929   0.9325
   8.750   0.8047   0.03059   0.02196   0.0103   0.3865   0.9488
   9.000   0.8293   0.03174   0.02318   0.0086   0.3796   0.9686
   9.250   0.8662   0.03220   0.02359   0.0061   0.3740   0.9860
   9.500   0.8999   0.03290   0.02422   0.0041   0.3689   1.0000
   9.750   0.8841   0.03419   0.02556   0.0087   0.3634   1.0000
  10.000   0.8863   0.03499   0.02632   0.0113   0.3581   1.0000
  10.250   0.9037   0.03523   0.02647   0.0125   0.3539   1.0000
  10.500   0.9086   0.03615   0.02738   0.0146   0.3492   1.0000
  10.750   0.8983   0.03790   0.02921   0.0177   0.3435   1.0000
  11.000   0.9064   0.03877   0.03005   0.0194   0.3386   1.0000
  11.250   0.9295   0.03884   0.03004   0.0200   0.3347   1.0000
  11.500   0.9226   0.04069   0.03195   0.0224   0.3294   1.0000
  11.750   0.9139   0.04277   0.03411   0.0247   0.3237   1.0000
  12.000   0.9270   0.04349   0.03480   0.0257   0.3192   1.0000
  12.250   0.9557   0.04323   0.03444   0.0260   0.3157   1.0000
  12.500   0.9277   0.04690   0.03828   0.0287   0.3095   1.0000
  12.750   0.9234   0.04904   0.04048   0.0302   0.3041   1.0000
  13.000   0.9443   0.04926   0.04064   0.0307   0.3002   1.0000
  13.250   0.9549   0.05033   0.04170   0.0315   0.2959   1.0000
  13.500   0.9147   0.05579   0.04736   0.0334   0.2887   1.0000
  13.750   0.9290   0.05659   0.04814   0.0340   0.2844   1.0000
  14.000   0.9632   0.05560   0.04704   0.0342   0.2812   1.0000
  14.250   0.8876   0.06525   0.05700   0.0353   0.2718   1.0000
  14.500   0.9050   0.06579   0.05751   0.0357   0.2678   1.0000
  14.750   0.9445   0.06398   0.05559   0.0362   0.2650   1.0000
  15.000   0.8462   0.07761   0.06954   0.0354   0.2528   1.0000
  15.250   0.8839   0.07567   0.06753   0.0360   0.2505   1.0000
  15.500   0.9302   0.07279   0.06454   0.0367   0.2484   1.0000
  15.750   0.8315   0.08772   0.07976   0.0345   0.2351   1.0000
  16.000   0.8736   0.08498   0.07695   0.0354   0.2337   1.0000
  16.500   0.7960   0.10139   0.09357   0.0319   0.2149   1.0000
  16.750   0.8643   0.09471   0.08676   0.0339   0.2170   1.0000
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