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Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Rhode St. Genese 30 (rhodesg30-il)
Reynolds number: 100,000
Max Cl/Cd: 51.31 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rhodesg30-il-100000.txt
Download as CSV file: xf-rhodesg30-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Rhode St. Genese 30                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3284   0.09268   0.08807  -0.0333   1.0000   0.0966
 -10.500  -0.3958   0.09698   0.09203  -0.0289   1.0000   0.0894
 -10.250  -0.3970   0.09395   0.08907  -0.0301   1.0000   0.0938
 -10.000  -0.4120   0.09101   0.08624  -0.0337   1.0000   0.0963
  -9.750  -0.4359   0.08806   0.08345  -0.0374   1.0000   0.0970
  -9.500  -0.4519   0.08412   0.07956  -0.0417   1.0000   0.0973
  -9.250  -0.4149   0.08152   0.07697  -0.0319   1.0000   0.1040
  -9.000  -0.4818   0.06304   0.05832  -0.0470   1.0000   0.0587
  -8.750  -0.4885   0.05867   0.05388  -0.0458   1.0000   0.0585
  -8.500  -0.4955   0.05400   0.04906  -0.0446   1.0000   0.0583
  -8.250  -0.5041   0.04823   0.04291  -0.0433   1.0000   0.0587
  -8.000  -0.4943   0.04764   0.04254  -0.0410   1.0000   0.0616
  -7.750  -0.4904   0.04442   0.03912  -0.0394   1.0000   0.0649
  -7.500  -0.4923   0.03734   0.03090  -0.0382   1.0000   0.0708
  -7.250  -0.4777   0.03708   0.03099  -0.0367   1.0000   0.0761
  -7.000  -0.4648   0.03520   0.02858  -0.0352   1.0000   0.0827
  -6.750  -0.4496   0.03351   0.02634  -0.0338   1.0000   0.0840
  -6.500  -0.4339   0.03372   0.02702  -0.0326   1.0000   0.0907
  -6.250  -0.4174   0.03284   0.02579  -0.0313   1.0000   0.0953
  -6.000  -0.4019   0.03299   0.02608  -0.0301   1.0000   0.1031
  -5.750  -0.3844   0.03202   0.02490  -0.0291   1.0000   0.1046
  -5.500  -0.3660   0.03106   0.02370  -0.0281   1.0000   0.1056
  -5.250  -0.3472   0.03023   0.02263  -0.0272   1.0000   0.1069
  -5.000  -0.3282   0.02980   0.02184  -0.0262   1.0000   0.1102
  -4.750  -0.2882   0.02968   0.02188  -0.0299   0.9927   0.1208
  -4.500  -0.2381   0.02886   0.02064  -0.0346   0.9832   0.1234
  -4.250  -0.1952   0.02818   0.02003  -0.0384   0.9726   0.1332
  -4.000  -0.1491   0.02670   0.01792  -0.0415   0.9622   0.1266
  -3.750  -0.1019   0.02572   0.01669  -0.0450   0.9527   0.1242
  -3.500  -0.0580   0.02454   0.01537  -0.0479   0.9437   0.1224
  -3.250  -0.0200   0.02363   0.01433  -0.0497   0.9345   0.1211
  -3.000   0.0271   0.02271   0.01330  -0.0531   0.9276   0.1202
  -2.750   0.0633   0.02200   0.01253  -0.0544   0.9174   0.1199
  -2.500   0.1151   0.02117   0.01168  -0.0584   0.9115   0.1219
  -2.250   0.1518   0.02066   0.01114  -0.0597   0.9003   0.1248
  -2.000   0.1929   0.01983   0.01047  -0.0618   0.8910   0.1283
  -1.750   0.2365   0.01906   0.00980  -0.0640   0.8825   0.1320
  -1.500   0.2693   0.01857   0.00933  -0.0642   0.8699   0.1364
  -1.250   0.3028   0.01802   0.00884  -0.0645   0.8571   0.1440
  -1.000   0.3365   0.01742   0.00834  -0.0647   0.8437   0.1616
  -0.750   0.4327   0.01419   0.00754  -0.0765   0.8351   1.0000
  -0.500   0.4558   0.01405   0.00726  -0.0747   0.8139   1.0000
  -0.250   0.4824   0.01381   0.00688  -0.0733   0.7928   1.0000
   0.000   0.5059   0.01364   0.00659  -0.0715   0.7668   1.0000
   0.250   0.5302   0.01350   0.00629  -0.0697   0.7370   1.0000
   0.500   0.5546   0.01345   0.00603  -0.0681   0.7028   1.0000
   0.750   0.5775   0.01358   0.00591  -0.0664   0.6641   1.0000
   1.000   0.6007   0.01384   0.00590  -0.0650   0.6294   1.0000
   1.250   0.6239   0.01419   0.00601  -0.0637   0.6003   1.0000
   1.500   0.6478   0.01456   0.00621  -0.0628   0.5783   1.0000
   1.750   0.6719   0.01496   0.00648  -0.0620   0.5604   1.0000
   2.000   0.6966   0.01537   0.00679  -0.0614   0.5465   1.0000
   2.250   0.7221   0.01579   0.00709  -0.0609   0.5355   1.0000
   2.500   0.7467   0.01621   0.00753  -0.0603   0.5245   1.0000
   2.750   0.7714   0.01664   0.00795  -0.0598   0.5144   1.0000
   3.000   0.7968   0.01706   0.00830  -0.0593   0.5050   1.0000
   3.250   0.8210   0.01749   0.00880  -0.0587   0.4953   1.0000
   3.500   0.8452   0.01791   0.00924  -0.0580   0.4849   1.0000
   3.750   0.8689   0.01829   0.00958  -0.0572   0.4726   1.0000
   4.000   0.8915   0.01862   0.00990  -0.0562   0.4577   1.0000
   4.250   0.9138   0.01896   0.01021  -0.0552   0.4425   1.0000
   4.500   0.9367   0.01933   0.01058  -0.0542   0.4290   1.0000
   4.750   0.9603   0.01975   0.01103  -0.0535   0.4177   1.0000
   5.000   0.9822   0.02013   0.01154  -0.0525   0.4051   1.0000
   5.250   1.0040   0.02050   0.01200  -0.0514   0.3919   1.0000
   5.500   1.0249   0.02080   0.01239  -0.0502   0.3769   1.0000
   5.750   1.0444   0.02102   0.01267  -0.0487   0.3589   1.0000
   6.000   1.0623   0.02118   0.01292  -0.0469   0.3393   1.0000
   6.250   1.0767   0.02122   0.01315  -0.0445   0.3131   1.0000
   6.500   1.0863   0.02117   0.01329  -0.0412   0.2596   1.0000
   6.750   1.0813   0.02308   0.01422  -0.0367   0.1439   1.0000
   7.000   1.0842   0.02510   0.01602  -0.0334   0.1173   1.0000
   7.250   1.0914   0.02661   0.01754  -0.0305   0.1058   1.0000
   7.500   1.0981   0.02810   0.01900  -0.0277   0.0980   1.0000
   7.750   1.1071   0.02935   0.02029  -0.0252   0.0910   1.0000
   8.000   1.1153   0.03084   0.02175  -0.0227   0.0861   1.0000
   8.250   1.1282   0.03218   0.02316  -0.0207   0.0811   1.0000
   8.500   1.1442   0.03400   0.02479  -0.0196   0.0758   1.0000
   8.750   1.1646   0.03567   0.02667  -0.0186   0.0721   1.0000
   9.000   1.1843   0.03750   0.02853  -0.0178   0.0676   1.0000
   9.250   1.2176   0.04076   0.03180  -0.0192   0.0635   1.0000
   9.500   1.2350   0.04333   0.03471  -0.0180   0.0614   1.0000
   9.750   1.2469   0.04581   0.03746  -0.0165   0.0588   1.0000
  10.000   1.2574   0.04844   0.04027  -0.0150   0.0566   1.0000
  10.250   1.2672   0.05179   0.04387  -0.0137   0.0552   1.0000
  10.500   1.2706   0.05541   0.04777  -0.0117   0.0547   1.0000
  10.750   1.2664   0.05887   0.05152  -0.0091   0.0545   1.0000
  11.000   1.2579   0.06262   0.05554  -0.0067   0.0542   1.0000
  11.250   1.2448   0.06644   0.05962  -0.0044   0.0539   1.0000
  11.500   1.2280   0.06985   0.06329  -0.0024   0.0540   1.0000
  11.750   1.2090   0.07399   0.06767  -0.0014   0.0539   1.0000
  12.000   1.1873   0.07786   0.07179  -0.0009   0.0541   1.0000
  12.250   0.9943   0.08454   0.07943  -0.0019   0.0596   1.0000
  12.500   0.9550   0.09290   0.08800  -0.0060   0.0607   1.0000
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