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NPL 9510 AIRFOIL (npl9510-il)

NPL 9510 AIRFOIL - NPL 9510 transonic airfoil


Airfoil npl9510-il
Details Dat file Parser  
(npl9510-il) NPL 9510 AIRFOIL
NPL 9510 transonic airfoil
Max thickness 11.1% at 32% chord.
Max camber 1.6% at 80% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NPL 9510 AIRFOIL
       62.       40.

 0.0       0.0
 0.0004098 0.0039390
 0.0016188 0.0076160
 0.0025234 0.0094337
 0.0050317 0.0127776
 0.0100414 0.0166951
 0.0150476 0.0192027
 0.0200519 0.0209703
 0.0250553 0.0223379
 0.0300581 0.0235155
 0.0400629 0.0254507
 0.0500670 0.0271159
 0.0600706 0.0285811
 0.0700737 0.0299163
 0.0800766 0.0311115
 0.0900794 0.0322067
 0.1000817 0.0332019
 0.1200861 0.0350223
 0.1400899 0.0366127
 0.1600933 0.0380131
 0.1800964 0.0392735
 0.2000991 0.0404238
 0.2201018 0.0415241
 0.2401043 0.0425746
 0.2601064 0.0435450
 0.2801085 0.0443953
 0.3001103 0.0451957
 0.3201120 0.0459161
 0.3401136 0.0465865
 0.3601150 0.0471869
 0.3801164 0.0477473
 0.4001172 0.0481977
 0.4201180 0.0485681
 0.4401186 0.0488285
 0.4601190 0.0490089
 0.4801190 0.0490993
 0.5001190 0.0490897
 0.5201187 0.0490100
 0.5401183 0.0488405
 0.5601174 0.0485809
 0.5801165 0.0482813
 0.6001153 0.0478316
 0.6201138 0.0472721
 0.6401120 0.0466125
 0.6601100 0.0457928
 0.6801076 0.0448833
 0.7001047 0.0437137
 0.7201012 0.0423841
 0.7400972 0.0408145
 0.7600926 0.0390649
 0.7800876 0.0371055
 0.8000821 0.0349158
 0.8200762 0.0325763
 0.8400697 0.0299867
 0.8600628 0.0272171
 0.8800553 0.0242575
 0.9000475 0.0211579
 0.9200392 0.0178283
 0.9400302 0.0142387
 0.9600205 0.0104192
 0.9800107 0.0064696
 1.0000000 0.0024400

 0.0       0.0
 0.0003901 -.0039510
 0.0015803 -.0079339
 0.0024758 -.0097461
 0.0049665 -.0135223
 0.0099541 -.0184647
 0.0149453 -.0220271
 0.0199379 -.0250095
 0.0249314 -.0275719
 0.0299257 -.0298943
 0.0399156 -.0339591
 0.0499067 -.0374839
 0.0598991 -.0405586
 0.0698923 -.0432534
 0.0798863 -.0456482
 0.0898811 -.0477329
 0.0998764 -.0496277
 0.1198680 -.0529273
 0.1598553 -.0579664
 0.1998461 -.0616157
 0.2398401 -.0639746
 0.2798371 -.0650539
 0.3198372 -.0648530
 0.3605409 -.0633439
 0.3998474 -.0605916
 0.4398572 -.0566009
 0.4798696 -.0515300
 0.5198842 -.0455493
 0.5599002 -.0389885
 0.5999170 -.0321379
 0.6399337 -.0252971
 0.6799499 -.0187163
 0.7198653 -.0124053
 0.7599786 -.0068948
 0.7999896 -.0024340
 0.8399976 0.0009268
 0.8800016 0.0025876
 0.9200013 0.0025884
 0.9599968 0.0008592
 1.0000000 -.0024400
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Lednicer format dat file
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Polars for NPL 9510 AIRFOIL (npl9510-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   npl9510-il50,000915.5 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9510-il50,000517 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   npl9510-il100,000918.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9510-il100,000523.3 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   npl9510-il200,000925.4 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9510-il200,000532.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   npl9510-il500,000940.3 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9510-il500,000549.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   npl9510-il1,000,000957.2 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9510-il1,000,000567.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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