Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Dayton-Wright T-1 (daytonwrightt1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Dayton-Wright T-1 (daytonwrightt1-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103.44 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-daytonwrightt1-il-1000000-n5.txt
Download as CSV file: xf-daytonwrightt1-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Dayton-Wright T-1                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -0.7269   0.09561   0.09332  -0.0659   1.0000   0.0220
 -17.750  -0.8185   0.07694   0.07441  -0.0787   1.0000   0.0220
 -17.500  -0.8888   0.06325   0.06056  -0.0886   1.0000   0.0220
 -17.250  -1.0259   0.03814   0.03508  -0.1118   1.0000   0.0217
 -17.000  -1.0222   0.03298   0.02968  -0.1178   0.9953   0.0218
 -16.750  -1.0130   0.03056   0.02711  -0.1192   0.9901   0.0220
 -16.500  -0.9990   0.02882   0.02526  -0.1197   0.9845   0.0221
 -16.250  -0.9821   0.02743   0.02376  -0.1198   0.9794   0.0223
 -16.000  -0.9645   0.02621   0.02243  -0.1195   0.9737   0.0225
 -15.750  -0.9461   0.02510   0.02121  -0.1191   0.9688   0.0227
 -15.500  -0.9293   0.02407   0.02007  -0.1182   0.9623   0.0229
 -15.250  -0.9106   0.02312   0.01901  -0.1173   0.9569   0.0230
 -15.000  -0.8925   0.02228   0.01806  -0.1162   0.9503   0.0232
 -14.750  -0.8729   0.02149   0.01717  -0.1152   0.9446   0.0233
 -14.500  -0.8522   0.02079   0.01637  -0.1142   0.9395   0.0234
 -14.250  -0.8306   0.02019   0.01568  -0.1133   0.9337   0.0236
 -14.000  -0.8085   0.01961   0.01500  -0.1124   0.9283   0.0237
 -13.750  -0.7861   0.01903   0.01433  -0.1116   0.9234   0.0238
 -13.500  -0.7662   0.01814   0.01334  -0.1105   0.9176   0.0240
 -13.250  -0.7452   0.01737   0.01248  -0.1095   0.9122   0.0242
 -13.000  -0.7226   0.01674   0.01177  -0.1086   0.9073   0.0244
 -12.750  -0.6992   0.01619   0.01116  -0.1078   0.9016   0.0247
 -12.500  -0.6753   0.01571   0.01059  -0.1071   0.8956   0.0249
 -12.250  -0.6508   0.01526   0.01008  -0.1064   0.8899   0.0251
 -12.000  -0.6259   0.01484   0.00960  -0.1057   0.8840   0.0253
 -11.750  -0.6008   0.01444   0.00913  -0.1050   0.8787   0.0255
 -11.500  -0.5753   0.01406   0.00868  -0.1045   0.8739   0.0257
 -11.250  -0.5495   0.01370   0.00827  -0.1039   0.8688   0.0260
 -11.000  -0.5235   0.01337   0.00788  -0.1034   0.8636   0.0263
 -10.750  -0.4974   0.01305   0.00750  -0.1029   0.8589   0.0266
 -10.500  -0.4712   0.01271   0.00711  -0.1024   0.8540   0.0268
 -10.250  -0.4448   0.01240   0.00674  -0.1019   0.8487   0.0270
  -9.750  -0.3916   0.01182   0.00605  -0.1010   0.8390   0.0275
  -9.500  -0.3647   0.01156   0.00573  -0.1006   0.8338   0.0277
  -9.250  -0.3378   0.01132   0.00543  -0.1002   0.8285   0.0278
  -9.000  -0.3106   0.01109   0.00516  -0.0998   0.8236   0.0280
  -8.750  -0.2837   0.01080   0.00483  -0.0995   0.8180   0.0283
  -8.500  -0.2570   0.01052   0.00449  -0.0990   0.8125   0.0288
  -8.250  -0.2298   0.01028   0.00422  -0.0987   0.8072   0.0293
  -8.000  -0.2024   0.01006   0.00397  -0.0984   0.8012   0.0298
  -7.750  -0.1751   0.00988   0.00375  -0.0981   0.7952   0.0302
  -7.500  -0.1475   0.00970   0.00355  -0.0978   0.7894   0.0308
  -7.250  -0.1199   0.00953   0.00335  -0.0975   0.7827   0.0313
  -7.000  -0.0924   0.00940   0.00317  -0.0972   0.7761   0.0319
  -6.750  -0.0646   0.00926   0.00301  -0.0970   0.7690   0.0325
  -6.500  -0.0372   0.00914   0.00284  -0.0967   0.7613   0.0331
  -6.250  -0.0096   0.00898   0.00267  -0.0964   0.7534   0.0343
  -6.000   0.0175   0.00887   0.00252  -0.0961   0.7436   0.0357
  -5.750   0.0445   0.00878   0.00238  -0.0957   0.7294   0.0373
  -5.500   0.0709   0.00872   0.00225  -0.0952   0.7115   0.0397
  -5.250   0.0972   0.00865   0.00213  -0.0947   0.6933   0.0445
  -5.000   0.1233   0.00854   0.00203  -0.0943   0.6773   0.0552
  -4.750   0.1493   0.00849   0.00195  -0.0937   0.6574   0.0669
  -4.500   0.1750   0.00849   0.00189  -0.0932   0.6358   0.0753
  -4.250   0.2013   0.00849   0.00184  -0.0927   0.6180   0.0822
  -4.000   0.2280   0.00846   0.00180  -0.0924   0.6063   0.0901
  -3.750   0.2546   0.00844   0.00176  -0.0921   0.5941   0.0994
  -3.500   0.2813   0.00842   0.00173  -0.0917   0.5810   0.1097
  -3.250   0.3079   0.00840   0.00171  -0.0914   0.5677   0.1227
  -3.000   0.3343   0.00839   0.00170  -0.0911   0.5551   0.1372
  -2.750   0.3609   0.00840   0.00170  -0.0908   0.5431   0.1499
  -2.250   0.4139   0.00838   0.00171  -0.0902   0.5187   0.1831
  -2.000   0.4400   0.00838   0.00173  -0.0898   0.5060   0.2061
  -1.750   0.4660   0.00841   0.00177  -0.0895   0.4925   0.2285
  -1.500   0.4922   0.00846   0.00181  -0.0891   0.4783   0.2456
  -1.250   0.5183   0.00853   0.00186  -0.0888   0.4632   0.2589
  -1.000   0.5441   0.00863   0.00192  -0.0884   0.4464   0.2720
  -0.750   0.5695   0.00875   0.00200  -0.0880   0.4284   0.2865
  -0.500   0.5949   0.00888   0.00208  -0.0876   0.4106   0.2997
  -0.250   0.6203   0.00900   0.00217  -0.0872   0.3942   0.3163
   0.000   0.6457   0.00911   0.00227  -0.0868   0.3787   0.3348
   0.250   0.6711   0.00923   0.00236  -0.0864   0.3642   0.3506
   0.500   0.6966   0.00935   0.00247  -0.0861   0.3510   0.3651
   0.750   0.7220   0.00948   0.00257  -0.0857   0.3392   0.3806
   1.000   0.7471   0.00960   0.00269  -0.0853   0.3278   0.4002
   1.250   0.7727   0.00968   0.00280  -0.0850   0.3184   0.4250
   1.500   0.7971   0.00968   0.00293  -0.0846   0.3097   0.4899
   1.750   0.8107   0.00882   0.00312  -0.0818   0.3029   0.8842
   2.000   0.8402   0.00893   0.00334  -0.0822   0.2947   0.9509
   2.250   0.8795   0.00913   0.00352  -0.0849   0.2873   0.9766
   2.500   0.9118   0.00936   0.00370  -0.0862   0.2798   0.9860
   2.750   0.9438   0.00954   0.00385  -0.0874   0.2732   0.9927
   3.250   1.0115   0.01000   0.00422  -0.0908   0.2567   0.9991
   3.500   1.0366   0.01020   0.00438  -0.0906   0.2506   1.0000
   3.750   1.0566   0.01038   0.00453  -0.0892   0.2461   1.0000
   4.000   1.0777   0.01051   0.00467  -0.0881   0.2433   1.0000
   4.250   1.0982   0.01067   0.00482  -0.0868   0.2393   1.0000
   4.500   1.1180   0.01087   0.00499  -0.0855   0.2342   1.0000
   4.750   1.1380   0.01108   0.00518  -0.0842   0.2299   1.0000
   5.000   1.1596   0.01124   0.00535  -0.0832   0.2276   1.0000
   5.250   1.1803   0.01141   0.00553  -0.0821   0.2250   1.0000
   5.500   1.1998   0.01161   0.00573  -0.0807   0.2209   1.0000
   5.750   1.2182   0.01189   0.00598  -0.0793   0.2151   1.0000
   6.000   1.2390   0.01209   0.00619  -0.0783   0.2119   1.0000
   6.250   1.2598   0.01232   0.00642  -0.0773   0.2077   1.0000
   6.500   1.2794   0.01261   0.00670  -0.0762   0.2021   1.0000
   6.750   1.2995   0.01290   0.00698  -0.0752   0.1971   1.0000
   7.000   1.3200   0.01318   0.00726  -0.0743   0.1914   1.0000
   7.250   1.3386   0.01357   0.00761  -0.0732   0.1840   1.0000
   7.500   1.3578   0.01393   0.00796  -0.0722   0.1746   1.0000
   7.750   1.3732   0.01450   0.00843  -0.0706   0.1577   1.0000
   8.000   1.3835   0.01537   0.00913  -0.0684   0.1320   1.0000
   8.250   1.3925   0.01633   0.00996  -0.0660   0.1106   1.0000
   8.500   1.4053   0.01710   0.01068  -0.0643   0.0990   1.0000
   8.750   1.4185   0.01786   0.01141  -0.0627   0.0898   1.0000
   9.000   1.4318   0.01864   0.01215  -0.0611   0.0821   1.0000
   9.250   1.4464   0.01934   0.01285  -0.0599   0.0759   1.0000
   9.500   1.4593   0.02017   0.01365  -0.0585   0.0691   1.0000
   9.750   1.4706   0.02112   0.01457  -0.0569   0.0603   1.0000
  10.000   1.4777   0.02236   0.01573  -0.0549   0.0464   1.0000
  10.250   1.4756   0.02427   0.01751  -0.0521   0.0273   1.0000
  10.750   1.4897   0.02698   0.02022  -0.0489   0.0174   1.0000
  11.000   1.4993   0.02820   0.02148  -0.0477   0.0158   1.0000
  11.250   1.5087   0.02947   0.02279  -0.0465   0.0147   1.0000
  11.500   1.5168   0.03087   0.02422  -0.0454   0.0137   1.0000
  11.750   1.5255   0.03225   0.02565  -0.0444   0.0132   1.0000
  12.000   1.5341   0.03369   0.02714  -0.0435   0.0127   1.0000
  12.250   1.5416   0.03526   0.02877  -0.0427   0.0123   1.0000
  12.500   1.5479   0.03699   0.03056  -0.0418   0.0118   1.0000
  12.750   1.5530   0.03888   0.03250  -0.0411   0.0114   1.0000
  13.000   1.5570   0.04095   0.03463  -0.0404   0.0110   1.0000
  13.250   1.5603   0.04315   0.03690  -0.0398   0.0107   1.0000
  13.500   1.5648   0.04531   0.03913  -0.0394   0.0105   1.0000
  13.750   1.5681   0.04762   0.04151  -0.0391   0.0103   1.0000
  14.000   1.5703   0.05012   0.04410  -0.0388   0.0100   1.0000
  14.250   1.5714   0.05283   0.04687  -0.0387   0.0098   1.0000
  14.500   1.5712   0.05574   0.04986  -0.0386   0.0095   1.0000
  14.750   1.5697   0.05886   0.05306  -0.0387   0.0093   1.0000
  15.000   1.5667   0.06222   0.05651  -0.0389   0.0091   1.0000
  15.250   1.5621   0.06586   0.06023  -0.0392   0.0090   1.0000
  15.500   1.5560   0.06979   0.06425  -0.0396   0.0088   1.0000
  15.750   1.5480   0.07402   0.06857  -0.0402   0.0087   1.0000
  16.000   1.5386   0.07850   0.07315  -0.0409   0.0085   1.0000
  16.250   1.5290   0.08310   0.07785  -0.0417   0.0084   1.0000
  16.500   1.5201   0.08768   0.08254  -0.0427   0.0083   1.0000
  16.750   1.5099   0.09251   0.08747  -0.0438   0.0083   1.0000
  17.000   1.4988   0.09750   0.09256  -0.0450   0.0082   1.0000
  17.250   1.4875   0.10260   0.09776  -0.0464   0.0081   1.0000
  17.500   1.4761   0.10778   0.10305  -0.0479   0.0081   1.0000
  17.750   1.4647   0.11300   0.10837  -0.0495   0.0080   1.0000
<< Back to Dayton-Wright T-1 (daytonwrightt1-il)

Polar data table (+)

Polar graphs


<< Back to Dayton-Wright T-1 (daytonwrightt1-il)