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RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAF 30 AIRFOIL (raf30-il)
Reynolds number: 100,000
Max Cl/Cd: 39.14 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf30-il-100000-n5.txt
Download as CSV file: xf-raf30-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 30 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7920   0.09677   0.09105  -0.0258   1.0000   0.0390
 -14.000  -0.8612   0.08021   0.07415  -0.0371   1.0000   0.0374
 -13.750  -0.8951   0.07201   0.06569  -0.0419   1.0000   0.0371
 -13.500  -0.9162   0.06646   0.05993  -0.0444   1.0000   0.0373
 -13.250  -0.9329   0.06190   0.05516  -0.0458   1.0000   0.0376
 -13.000  -0.9460   0.05809   0.05115  -0.0464   1.0000   0.0381
 -12.750  -0.9574   0.05464   0.04748  -0.0462   1.0000   0.0385
 -12.500  -0.9666   0.05163   0.04425  -0.0455   1.0000   0.0392
 -12.250  -0.9738   0.04888   0.04125  -0.0442   1.0000   0.0399
 -12.000  -0.9786   0.04636   0.03847  -0.0424   1.0000   0.0406
 -11.750  -0.9803   0.04414   0.03597  -0.0404   1.0000   0.0413
 -11.500  -0.9813   0.04226   0.03379  -0.0378   1.0000   0.0421
 -11.250  -0.9720   0.04025   0.03176  -0.0364   1.0000   0.0434
 -11.000  -0.9635   0.03876   0.03023  -0.0346   1.0000   0.0446
 -10.750  -0.9548   0.03733   0.02871  -0.0326   1.0000   0.0459
 -10.500  -0.9441   0.03585   0.02707  -0.0307   1.0000   0.0471
 -10.250  -0.9323   0.03449   0.02555  -0.0289   1.0000   0.0488
 -10.000  -0.9191   0.03321   0.02406  -0.0271   1.0000   0.0505
  -9.750  -0.9045   0.03182   0.02259  -0.0256   1.0000   0.0521
  -9.500  -0.8908   0.03058   0.02135  -0.0239   1.0000   0.0536
  -9.250  -0.8771   0.02948   0.02020  -0.0221   1.0000   0.0551
  -9.000  -0.8633   0.02849   0.01915  -0.0202   1.0000   0.0573
  -8.750  -0.8491   0.02754   0.01810  -0.0182   1.0000   0.0598
  -8.500  -0.8350   0.02661   0.01709  -0.0162   1.0000   0.0620
  -8.250  -0.8236   0.02560   0.01611  -0.0138   1.0000   0.0644
  -8.000  -0.8106   0.02474   0.01522  -0.0116   1.0000   0.0672
  -7.750  -0.7971   0.02393   0.01433  -0.0093   1.0000   0.0708
  -7.500  -0.7840   0.02312   0.01351  -0.0070   1.0000   0.0753
  -7.250  -0.7704   0.02234   0.01275  -0.0048   1.0000   0.0826
  -7.000  -0.7571   0.02154   0.01200  -0.0025   1.0000   0.0923
  -6.750  -0.7436   0.02076   0.01128  -0.0002   1.0000   0.1063
  -6.500  -0.7297   0.02003   0.01059   0.0020   1.0000   0.1245
  -6.250  -0.7158   0.01935   0.01000   0.0042   1.0000   0.1454
  -6.000  -0.7020   0.01870   0.00947   0.0065   1.0000   0.1704
  -5.750  -0.6885   0.01809   0.00903   0.0087   1.0000   0.2006
  -5.500  -0.6752   0.01754   0.00864   0.0110   1.0000   0.2355
  -5.250  -0.6618   0.01706   0.00832   0.0134   1.0000   0.2732
  -5.000  -0.6488   0.01662   0.00804   0.0157   1.0000   0.3118
  -4.750  -0.6337   0.01619   0.00782   0.0177   0.9991   0.3548
  -4.500  -0.6005   0.01575   0.00763   0.0161   0.9904   0.4095
  -4.250  -0.5666   0.01545   0.00750   0.0146   0.9819   0.4560
  -4.000  -0.5322   0.01525   0.00736   0.0131   0.9732   0.4913
  -3.750  -0.4990   0.01507   0.00721   0.0120   0.9636   0.5213
  -3.500  -0.4651   0.01492   0.00708   0.0107   0.9547   0.5494
  -3.250  -0.4295   0.01479   0.00696   0.0093   0.9465   0.5785
  -3.000  -0.3977   0.01469   0.00691   0.0087   0.9366   0.6093
  -2.750  -0.3600   0.01460   0.00688   0.0070   0.9300   0.6374
  -2.500  -0.3284   0.01451   0.00678   0.0064   0.9192   0.6578
  -2.250  -0.2927   0.01441   0.00668   0.0051   0.9108   0.6750
  -2.000  -0.2585   0.01433   0.00658   0.0041   0.9011   0.6912
  -1.750  -0.2253   0.01425   0.00650   0.0033   0.8907   0.7068
  -1.500  -0.1888   0.01417   0.00640   0.0019   0.8821   0.7221
  -1.250  -0.1582   0.01412   0.00634   0.0016   0.8699   0.7366
  -1.000  -0.1258   0.01408   0.00630   0.0011   0.8585   0.7502
  -0.750  -0.0923   0.01403   0.00625   0.0004   0.8474   0.7638
  -0.500  -0.0600   0.01400   0.00620  -0.0001   0.8347   0.7773
  -0.250  -0.0299   0.01397   0.00617  -0.0001   0.8202   0.7911
   0.000   0.0000   0.01397   0.00616   0.0000   0.8054   0.8054
   0.250   0.0299   0.01397   0.00617   0.0001   0.7910   0.8202
   0.500   0.0600   0.01400   0.00620   0.0001   0.7772   0.8347
   0.750   0.0923   0.01403   0.00625  -0.0004   0.7638   0.8474
   1.000   0.1258   0.01408   0.00630  -0.0011   0.7503   0.8585
   1.250   0.1582   0.01412   0.00634  -0.0016   0.7367   0.8699
   1.500   0.1889   0.01417   0.00640  -0.0019   0.7221   0.8821
   1.750   0.2254   0.01425   0.00650  -0.0033   0.7068   0.8907
   2.000   0.2585   0.01433   0.00658  -0.0041   0.6912   0.9010
   2.250   0.2927   0.01441   0.00668  -0.0051   0.6749   0.9107
   2.500   0.3285   0.01451   0.00678  -0.0064   0.6578   0.9192
   2.750   0.3600   0.01460   0.00688  -0.0070   0.6374   0.9300
   3.000   0.3978   0.01469   0.00691  -0.0087   0.6091   0.9366
   3.250   0.4295   0.01479   0.00697  -0.0093   0.5783   0.9465
   3.500   0.4651   0.01492   0.00708  -0.0107   0.5493   0.9547
   3.750   0.4990   0.01507   0.00721  -0.0120   0.5211   0.9636
   4.000   0.5322   0.01525   0.00736  -0.0131   0.4912   0.9732
   4.250   0.5665   0.01546   0.00749  -0.0146   0.4546   0.9819
   4.500   0.6005   0.01574   0.00763  -0.0161   0.4098   0.9904
   4.750   0.6337   0.01619   0.00782  -0.0177   0.3539   0.9991
   5.000   0.6488   0.01662   0.00804  -0.0157   0.3115   1.0000
   5.250   0.6618   0.01706   0.00832  -0.0134   0.2724   1.0000
   5.500   0.6752   0.01754   0.00864  -0.0110   0.2352   1.0000
   5.750   0.6886   0.01809   0.00903  -0.0087   0.2006   1.0000
   6.000   0.7020   0.01870   0.00947  -0.0065   0.1699   1.0000
   6.250   0.7158   0.01935   0.01000  -0.0042   0.1452   1.0000
   6.500   0.7298   0.02003   0.01059  -0.0020   0.1244   1.0000
   6.750   0.7436   0.02077   0.01128   0.0002   0.1060   1.0000
   7.000   0.7572   0.02154   0.01200   0.0025   0.0924   1.0000
   7.250   0.7704   0.02234   0.01275   0.0048   0.0826   1.0000
   7.500   0.7841   0.02311   0.01351   0.0070   0.0755   1.0000
   7.750   0.7971   0.02393   0.01434   0.0093   0.0707   1.0000
   8.000   0.8107   0.02474   0.01522   0.0116   0.0672   1.0000
   8.250   0.8237   0.02560   0.01611   0.0138   0.0645   1.0000
   8.500   0.8352   0.02660   0.01708   0.0162   0.0621   1.0000
   8.750   0.8492   0.02754   0.01810   0.0182   0.0598   1.0000
   9.000   0.8634   0.02849   0.01914   0.0201   0.0573   1.0000
   9.250   0.8772   0.02948   0.02021   0.0220   0.0552   1.0000
   9.500   0.8909   0.03057   0.02134   0.0239   0.0536   1.0000
   9.750   0.9045   0.03182   0.02259   0.0256   0.0520   1.0000
  10.000   0.9191   0.03320   0.02406   0.0271   0.0505   1.0000
  10.250   0.9324   0.03450   0.02556   0.0289   0.0487   1.0000
  10.500   0.9442   0.03586   0.02708   0.0307   0.0471   1.0000
  10.750   0.9550   0.03733   0.02870   0.0326   0.0459   1.0000
  11.000   0.9641   0.03881   0.03029   0.0345   0.0447   1.0000
  11.250   0.9722   0.04027   0.03179   0.0364   0.0434   1.0000
  11.500   0.9824   0.04228   0.03380   0.0377   0.0422   1.0000
  11.750   0.9804   0.04414   0.03598   0.0403   0.0413   1.0000
  12.000   0.9785   0.04635   0.03846   0.0424   0.0405   1.0000
  12.250   0.9741   0.04886   0.04123   0.0441   0.0398   1.0000
  12.500   0.9670   0.05162   0.04424   0.0454   0.0392   1.0000
  12.750   0.9578   0.05468   0.04752   0.0462   0.0386   1.0000
  13.000   0.9469   0.05802   0.05107   0.0463   0.0379   1.0000
  13.250   0.9341   0.06180   0.05505   0.0458   0.0375   1.0000
  13.500   0.9175   0.06635   0.05981   0.0444   0.0372   1.0000
  13.750   0.8947   0.07220   0.06589   0.0417   0.0373   1.0000
  14.000   0.8643   0.07983   0.07376   0.0373   0.0374   1.0000
  14.250   0.7937   0.09664   0.09091   0.0257   0.0389   1.0000
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