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

DSMA-523B AIRFOIL (dsma523b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: DSMA-523B AIRFOIL (dsma523b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 73.25 at α=-1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dsma523b-il-1000000.txt
Download as CSV file: xf-dsma523b-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DSMA-523B AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -1.1047   0.10514   0.10250  -0.0295   1.0000   0.0204
 -17.750  -1.1590   0.09049   0.08758  -0.0382   1.0000   0.0203
 -17.500  -1.1922   0.08045   0.07734  -0.0440   1.0000   0.0203
 -17.250  -1.2147   0.07272   0.06944  -0.0484   1.0000   0.0203
 -17.000  -1.2292   0.06669   0.06328  -0.0516   1.0000   0.0204
 -16.750  -1.2416   0.06134   0.05779  -0.0542   1.0000   0.0204
 -16.500  -1.2506   0.05685   0.05317  -0.0561   1.0000   0.0205
 -16.250  -1.2565   0.05306   0.04928  -0.0573   1.0000   0.0206
 -16.000  -1.2617   0.04968   0.04579  -0.0581   1.0000   0.0207
 -15.750  -1.2663   0.04665   0.04265  -0.0583   1.0000   0.0208
 -15.500  -1.2679   0.04411   0.04002  -0.0582   1.0000   0.0209
 -15.250  -1.2698   0.04168   0.03749  -0.0578   1.0000   0.0210
 -15.000  -1.2698   0.03955   0.03527  -0.0572   1.0000   0.0211
 -14.750  -1.2685   0.03766   0.03330  -0.0563   1.0000   0.0213
 -14.500  -1.2676   0.03589   0.03144  -0.0551   1.0000   0.0214
 -14.250  -1.2654   0.03440   0.02987  -0.0536   1.0000   0.0216
 -14.000  -1.2675   0.03292   0.02831  -0.0513   1.0000   0.0217
 -13.750  -1.2712   0.03153   0.02685  -0.0485   1.0000   0.0218
 -13.500  -1.2607   0.03030   0.02555  -0.0478   1.0000   0.0220
 -13.250  -1.2468   0.02914   0.02432  -0.0476   1.0000   0.0222
 -13.000  -1.2299   0.02811   0.02322  -0.0477   1.0000   0.0223
 -12.750  -1.2147   0.02647   0.02148  -0.0482   1.0000   0.0226
 -12.500  -1.1970   0.02482   0.01976  -0.0491   1.0000   0.0231
 -12.250  -1.1749   0.02370   0.01860  -0.0501   1.0000   0.0234
 -12.000  -1.1508   0.02278   0.01764  -0.0512   1.0000   0.0237
 -11.750  -1.1253   0.02198   0.01681  -0.0524   1.0000   0.0240
 -11.500  -1.0987   0.02125   0.01604  -0.0536   1.0000   0.0244
 -11.250  -1.0714   0.02056   0.01531  -0.0548   1.0000   0.0248
 -11.000  -1.0423   0.01992   0.01461  -0.0563   0.9999   0.0252
 -10.750  -1.0097   0.01931   0.01396  -0.0583   0.9995   0.0256
 -10.500  -0.9773   0.01878   0.01338  -0.0602   0.9990   0.0260
 -10.250  -0.9450   0.01833   0.01287  -0.0619   0.9985   0.0263
 -10.000  -0.9111   0.01737   0.01188  -0.0645   0.9983   0.0272
  -9.750  -0.8777   0.01683   0.01134  -0.0665   0.9978   0.0279
  -9.500  -0.8443   0.01642   0.01091  -0.0684   0.9973   0.0286
  -9.250  -0.8111   0.01604   0.01051  -0.0701   0.9969   0.0293
  -9.000  -0.7781   0.01571   0.01015  -0.0718   0.9965   0.0301
  -8.750  -0.7452   0.01544   0.00984  -0.0733   0.9961   0.0306
  -8.500  -0.7103   0.01488   0.00929  -0.0756   0.9960   0.0321
  -8.250  -0.6768   0.01459   0.00902  -0.0772   0.9957   0.0332
  -8.000  -0.6434   0.01435   0.00876  -0.0788   0.9954   0.0344
  -7.750  -0.6096   0.01409   0.00849  -0.0805   0.9951   0.0357
  -7.500  -0.5760   0.01389   0.00833  -0.0820   0.9948   0.0376
  -7.250  -0.5429   0.01376   0.00821  -0.0834   0.9946   0.0393
  -7.000  -0.5096   0.01364   0.00812  -0.0848   0.9943   0.0413
  -6.750  -0.4768   0.01361   0.00812  -0.0860   0.9940   0.0434
  -6.500  -0.4436   0.01361   0.00811  -0.0872   0.9937   0.0454
  -6.250  -0.4134   0.01344   0.00798  -0.0879   0.9922   0.0474
  -6.000  -0.3830   0.01341   0.00797  -0.0885   0.9913   0.0496
  -5.750  -0.3517   0.01337   0.00793  -0.0893   0.9905   0.0516
  -5.500  -0.3188   0.01323   0.00783  -0.0906   0.9900   0.0537
  -5.250  -0.2868   0.01319   0.00779  -0.0916   0.9894   0.0560
  -5.000  -0.2534   0.01305   0.00766  -0.0930   0.9890   0.0580
  -4.750  -0.2180   0.01281   0.00745  -0.0950   0.9888   0.0601
  -4.500  -0.1837   0.01268   0.00734  -0.0965   0.9884   0.0621
  -4.250  -0.1499   0.01261   0.00727  -0.0979   0.9880   0.0635
  -4.000  -0.1142   0.01242   0.00710  -0.0999   0.9878   0.0654
  -3.750  -0.0795   0.01229   0.00700  -0.1015   0.9876   0.0670
  -3.500  -0.0452   0.01220   0.00693  -0.1030   0.9873   0.0686
  -3.250  -0.0087   0.01210   0.00685  -0.1050   0.9868   0.0700
  -3.000   0.0444   0.01172   0.00650  -0.1103   0.9856   0.0722
  -2.750   0.0903   0.01114   0.00598  -0.1140   0.9808   0.0759
  -2.500   0.1401   0.01059   0.00560  -0.1188   0.9795   0.1067
  -2.250   0.1934   0.00996   0.00513  -0.1243   0.9783   0.1363
  -2.000   0.2386   0.00942   0.00477  -0.1281   0.9747   0.1803
  -1.750   0.3293   0.00789   0.00370  -0.1426   0.9727   0.3078
  -1.500   0.3949   0.00668   0.00301  -0.1516   0.9607   0.4785
  -1.250   0.4285   0.00585   0.00241  -0.1525   0.9176   0.5980
  -1.000   0.4346   0.00744   0.00278  -0.1471   0.6062   0.6149
  -0.750   0.4545   0.00871   0.00312  -0.1455   0.3781   0.6278
  -0.500   0.4794   0.00940   0.00341  -0.1447   0.2701   0.6387
  -0.250   0.5052   0.01005   0.00368  -0.1441   0.1853   0.6490
   0.000   0.5297   0.01069   0.00406  -0.1431   0.1117   0.6555
   0.250   0.5563   0.01108   0.00434  -0.1425   0.0897   0.6603
   0.500   0.5837   0.01140   0.00460  -0.1421   0.0795   0.6646
   0.750   0.6114   0.01173   0.00485  -0.1418   0.0710   0.6673
   1.000   0.6391   0.01187   0.00501  -0.1415   0.0672   0.6702
   1.250   0.6661   0.01212   0.00523  -0.1410   0.0626   0.6722
   1.500   0.6929   0.01240   0.00551  -0.1404   0.0592   0.6745
   1.750   0.7198   0.01265   0.00576  -0.1399   0.0565   0.6775
   2.000   0.7472   0.01291   0.00598  -0.1395   0.0535   0.6797
   2.250   0.7751   0.01316   0.00621  -0.1393   0.0510   0.6810
   2.500   0.8033   0.01333   0.00637  -0.1392   0.0493   0.6824
   2.750   0.8311   0.01354   0.00656  -0.1389   0.0474   0.6838
   3.000   0.8583   0.01386   0.00685  -0.1385   0.0454   0.6850
   3.250   0.8860   0.01413   0.00712  -0.1383   0.0438   0.6862
   3.500   0.9142   0.01423   0.00723  -0.1382   0.0427   0.6883
   3.750   0.9414   0.01442   0.00743  -0.1379   0.0415   0.6898
   4.000   0.9685   0.01465   0.00766  -0.1375   0.0403   0.6908
   4.250   0.9957   0.01495   0.00794  -0.1372   0.0389   0.6914
   4.500   1.0222   0.01536   0.00836  -0.1367   0.0377   0.6920
   4.750   1.0496   0.01555   0.00858  -0.1364   0.0370   0.6927
   5.000   1.0768   0.01579   0.00883  -0.1361   0.0361   0.6935
   5.250   1.1040   0.01603   0.00908  -0.1358   0.0352   0.6941
   5.500   1.1311   0.01628   0.00932  -0.1355   0.0343   0.6946
   5.750   1.1575   0.01662   0.00965  -0.1350   0.0334   0.6952
   6.000   1.1823   0.01725   0.01031  -0.1343   0.0322   0.6958
   6.250   1.2091   0.01749   0.01057  -0.1339   0.0318   0.6964
   6.500   1.2356   0.01778   0.01089  -0.1334   0.0312   0.6970
   6.750   1.2618   0.01810   0.01125  -0.1329   0.0306   0.6976
   7.000   1.2877   0.01844   0.01160  -0.1324   0.0300   0.6982
   7.250   1.3135   0.01876   0.01194  -0.1318   0.0294   0.6988
   7.500   1.3390   0.01913   0.01231  -0.1312   0.0288   0.6994
   7.750   1.3633   0.01965   0.01285  -0.1304   0.0282   0.7000
   8.000   1.3846   0.02066   0.01392  -0.1290   0.0274   0.7005
   8.250   1.4097   0.02100   0.01431  -0.1283   0.0272   0.7011
   8.500   1.4340   0.02144   0.01480  -0.1275   0.0269   0.7016
   8.750   1.4581   0.02189   0.01531  -0.1266   0.0266   0.7022
   9.000   1.4815   0.02239   0.01586  -0.1256   0.0262   0.7028
   9.250   1.5045   0.02292   0.01645  -0.1245   0.0259   0.7033
   9.500   1.5274   0.02342   0.01700  -0.1235   0.0255   0.7038
   9.750   1.5498   0.02393   0.01755  -0.1224   0.0251   0.7041
  10.000   1.5719   0.02444   0.01810  -0.1212   0.0248   0.7044
  10.250   1.5934   0.02498   0.01869  -0.1199   0.0245   0.7047
  10.500   1.6148   0.02552   0.01927  -0.1187   0.0242   0.7056
  10.750   1.6343   0.02622   0.02001  -0.1171   0.0238   0.7064
  11.000   1.6462   0.02786   0.02179  -0.1143   0.0231   0.7071
  11.250   1.6654   0.02843   0.02244  -0.1127   0.0230   0.7078
  11.500   1.6837   0.02901   0.02311  -0.1109   0.0228   0.7084
  11.750   1.7002   0.02971   0.02389  -0.1088   0.0226   0.7090
  12.000   1.7159   0.03039   0.02466  -0.1066   0.0223   0.7096
  12.250   1.7289   0.03124   0.02562  -0.1039   0.0221   0.7102
  12.500   1.7407   0.03213   0.02661  -0.1011   0.0219   0.7108
  12.750   1.7508   0.03307   0.02766  -0.0981   0.0217   0.7114
  13.000   1.7565   0.03404   0.02872  -0.0942   0.0215   0.7121
  13.250   1.7619   0.03511   0.02990  -0.0905   0.0213   0.7127
  13.500   1.7672   0.03631   0.03120  -0.0870   0.0212   0.7133
  13.750   1.7730   0.03748   0.03247  -0.0836   0.0210   0.7141
  14.000   1.7773   0.03881   0.03389  -0.0803   0.0208   0.7149
  14.250   1.7795   0.04034   0.03552  -0.0768   0.0207   0.7157
  14.500   1.7803   0.04201   0.03730  -0.0735   0.0206   0.7163
  14.750   1.7815   0.04370   0.03909  -0.0704   0.0204   0.7169
  15.000   1.7781   0.04589   0.04141  -0.0672   0.0204   0.7175
  15.250   1.7754   0.04811   0.04374  -0.0644   0.0202   0.7180
  15.500   1.7671   0.05104   0.04680  -0.0618   0.0202   0.7185
  15.750   1.7581   0.05426   0.05015  -0.0597   0.0201   0.7190
  16.000   1.7451   0.05822   0.05426  -0.0584   0.0200   0.7194
  16.250   1.7289   0.06308   0.05928  -0.0582   0.0199   0.7198
  16.500   1.7077   0.06943   0.06582  -0.0597   0.0199   0.7202
  16.750   1.6808   0.07787   0.07447  -0.0638   0.0199   0.7204
  17.000   1.6440   0.08990   0.08677  -0.0717   0.0199   0.7205
<< Back to DSMA-523B AIRFOIL (dsma523b-il)

Polar data table (+)

Polar graphs


<< Back to DSMA-523B AIRFOIL (dsma523b-il)