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TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il)
Reynolds number: 500,000
Max Cl/Cd: 88.29 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-tsagi-r-3a-il-500000-n5.txt
Download as CSV file: xf-tsagi-r-3a-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TsAGI R-3a (12%)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5150   0.11840   0.11611   0.0195   1.0045   0.0128
 -10.750  -0.5118   0.11430   0.11202   0.0177   1.0045   0.0128
  -9.250  -0.7138   0.03066   0.02688  -0.0347   1.0045   0.0121
  -9.000  -0.7017   0.02711   0.02288  -0.0342   1.0045   0.0122
  -8.750  -0.6830   0.02473   0.02016  -0.0339   0.9976   0.0123
  -8.500  -0.6536   0.02272   0.01782  -0.0352   0.9417   0.0124
  -8.250  -0.6331   0.02149   0.01621  -0.0339   0.8712   0.0125
  -7.750  -0.5912   0.01980   0.01368  -0.0313   0.7336   0.0128
  -7.500  -0.5672   0.01913   0.01263  -0.0306   0.6722   0.0129
  -7.250  -0.5426   0.01843   0.01160  -0.0301   0.6204   0.0130
  -7.000  -0.5179   0.01760   0.01053  -0.0296   0.5805   0.0132
  -6.750  -0.4922   0.01698   0.00974  -0.0293   0.5497   0.0134
  -6.500  -0.4659   0.01646   0.00907  -0.0289   0.5259   0.0136
  -6.250  -0.4394   0.01598   0.00845  -0.0286   0.5051   0.0138
  -6.000  -0.4126   0.01553   0.00787  -0.0283   0.4862   0.0141
  -5.750  -0.3856   0.01510   0.00732  -0.0280   0.4697   0.0143
  -5.500  -0.3586   0.01471   0.00680  -0.0277   0.4562   0.0146
  -5.250  -0.3313   0.01433   0.00632  -0.0274   0.4461   0.0149
  -5.000  -0.3039   0.01398   0.00587  -0.0272   0.4383   0.0152
  -4.750  -0.2762   0.01364   0.00547  -0.0269   0.4334   0.0155
  -4.500  -0.2486   0.01330   0.00507  -0.0267   0.4290   0.0159
  -4.250  -0.2210   0.01299   0.00471  -0.0264   0.4244   0.0166
  -4.000  -0.1931   0.01275   0.00442  -0.0262   0.4200   0.0173
  -3.750  -0.1650   0.01250   0.00414  -0.0260   0.4156   0.0179
  -3.500  -0.1369   0.01228   0.00387  -0.0258   0.4113   0.0186
  -3.250  -0.1089   0.01208   0.00364  -0.0256   0.4072   0.0196
  -3.000  -0.0807   0.01192   0.00345  -0.0254   0.4034   0.0209
  -2.750  -0.0523   0.01174   0.00329  -0.0253   0.4004   0.0233
  -2.500  -0.0239   0.01160   0.00315  -0.0251   0.3966   0.0278
  -2.250   0.0045   0.01148   0.00301  -0.0250   0.3927   0.0331
  -2.000   0.0328   0.01137   0.00288  -0.0248   0.3890   0.0383
  -1.750   0.0611   0.01126   0.00276  -0.0247   0.3856   0.0439
  -1.500   0.0896   0.01111   0.00265  -0.0246   0.3820   0.0514
  -1.250   0.1179   0.01096   0.00255  -0.0245   0.3775   0.0640
  -1.000   0.1461   0.01081   0.00247  -0.0244   0.3724   0.0921
  -0.750   0.1744   0.01066   0.00241  -0.0243   0.3675   0.1222
  -0.500   0.2027   0.01050   0.00236  -0.0242   0.3617   0.1562
  -0.250   0.2306   0.01030   0.00230  -0.0242   0.3554   0.2073
   0.000   0.2579   0.00992   0.00225  -0.0241   0.3493   0.3215
   0.250   0.2844   0.00943   0.00222  -0.0240   0.3414   0.4740
   0.750   0.3361   0.00877   0.00223  -0.0229   0.3212   0.7073
   1.000   0.3594   0.00850   0.00228  -0.0215   0.3071   0.8216
   1.250   0.3843   0.00842   0.00235  -0.0203   0.2919   0.9176
   1.500   0.4238   0.00855   0.00241  -0.0224   0.2790   0.9654
   1.750   0.4689   0.00872   0.00247  -0.0258   0.2699   0.9911
   2.000   0.5013   0.00888   0.00254  -0.0267   0.2637   0.9955
   2.250   0.5274   0.00904   0.00262  -0.0263   0.2586   0.9955
   2.500   0.5540   0.00916   0.00270  -0.0259   0.2546   0.9955
   2.750   0.5806   0.00930   0.00280  -0.0255   0.2505   0.9955
   3.000   0.6071   0.00947   0.00291  -0.0252   0.2465   0.9955
   3.250   0.6338   0.00965   0.00303  -0.0248   0.2426   0.9955
   3.500   0.6608   0.00978   0.00314  -0.0246   0.2395   0.9955
   3.750   0.6879   0.00992   0.00325  -0.0243   0.2360   0.9955
   4.000   0.7148   0.01010   0.00338  -0.0240   0.2321   0.9955
   4.250   0.7415   0.01030   0.00354  -0.0238   0.2283   0.9955
   4.500   0.7687   0.01045   0.00368  -0.0236   0.2263   0.9955
   4.750   0.7959   0.01060   0.00383  -0.0234   0.2242   0.9955
   5.000   0.8230   0.01076   0.00398  -0.0232   0.2217   0.9955
   5.250   0.8500   0.01093   0.00414  -0.0230   0.2190   0.9955
   5.500   0.8769   0.01113   0.00432  -0.0228   0.2164   0.9955
   5.750   0.9036   0.01135   0.00452  -0.0226   0.2140   0.9955
   6.000   0.9303   0.01156   0.00473  -0.0224   0.2119   0.9955
   6.250   0.9574   0.01172   0.00492  -0.0222   0.2102   0.9955
   6.500   0.9843   0.01189   0.00511  -0.0221   0.2080   0.9955
   6.750   1.0111   0.01208   0.00532  -0.0219   0.2053   0.9955
   7.000   1.0376   0.01229   0.00553  -0.0217   0.2024   0.9955
   7.250   1.0638   0.01254   0.00577  -0.0215   0.1995   0.9955
   7.500   1.0900   0.01278   0.00602  -0.0213   0.1970   0.9955
   7.750   1.1167   0.01296   0.00625  -0.0211   0.1948   0.9955
   8.000   1.1432   0.01316   0.00648  -0.0209   0.1919   0.9955
   8.250   1.1693   0.01339   0.00674  -0.0207   0.1886   0.9955
   8.500   1.1949   0.01366   0.00701  -0.0205   0.1853   0.9955
   8.750   1.2207   0.01391   0.00729  -0.0202   0.1821   0.9955
   9.000   1.2466   0.01412   0.00755  -0.0200   0.1773   0.9955
   9.250   1.2718   0.01442   0.00783  -0.0198   0.1716   0.9955
   9.500   1.2970   0.01470   0.00814  -0.0195   0.1661   0.9955
   9.750   1.3216   0.01503   0.00846  -0.0192   0.1593   0.9955
  10.000   1.3457   0.01539   0.00883  -0.0189   0.1524   0.9955
  10.250   1.3687   0.01586   0.00926  -0.0184   0.1447   0.9955
  10.500   1.3919   0.01629   0.00971  -0.0180   0.1387   0.9955
  10.750   1.4138   0.01682   0.01022  -0.0174   0.1336   0.9955
  11.000   1.4365   0.01725   0.01071  -0.0169   0.1302   0.9955
  11.250   1.4582   0.01775   0.01123  -0.0163   0.1263   0.9955
  11.500   1.4784   0.01836   0.01185  -0.0156   0.1223   0.9955
  11.750   1.4994   0.01886   0.01241  -0.0150   0.1186   0.9955
  12.000   1.5191   0.01945   0.01303  -0.0142   0.1141   0.9955
  12.250   1.5368   0.02016   0.01375  -0.0133   0.1104   0.9955
  12.500   1.5562   0.02069   0.01436  -0.0125   0.1080   0.9955
  12.750   1.5741   0.02130   0.01503  -0.0116   0.1052   0.9955
  13.000   1.5895   0.02204   0.01582  -0.0104   0.1020   0.9955
  13.250   1.6021   0.02286   0.01668  -0.0089   0.0990   0.9955
  13.500   1.6135   0.02363   0.01753  -0.0073   0.0957   0.9955
  13.750   1.6207   0.02474   0.01868  -0.0055   0.0914   0.9955
  14.000   1.6276   0.02599   0.01999  -0.0042   0.0880   0.9955
  14.250   1.6331   0.02750   0.02158  -0.0033   0.0838   0.9955
  14.500   1.6342   0.02966   0.02379  -0.0029   0.0796   0.9955
  14.750   1.6338   0.03231   0.02652  -0.0032   0.0743   0.9955
  15.000   1.6281   0.03598   0.03027  -0.0045   0.0690   0.9955
  15.250   1.6164   0.04077   0.03515  -0.0066   0.0639   0.9955
  15.500   1.5996   0.04632   0.04080  -0.0089   0.0588   0.9955
  15.750   1.5796   0.05220   0.04679  -0.0111   0.0556   0.9955
  16.000   1.5576   0.05825   0.05295  -0.0133   0.0530   0.9955
  16.250   1.5321   0.06463   0.05944  -0.0154   0.0509   0.9955
  16.500   1.5069   0.07096   0.06587  -0.0175   0.0491   0.9955
  16.750   1.4835   0.07720   0.07222  -0.0196   0.0476   0.9955
  17.000   1.4603   0.08370   0.07882  -0.0220   0.0458   0.9955
  17.250   1.4380   0.09031   0.08553  -0.0244   0.0442   0.9955
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