NPL 9510 AIRFOIL (npl9510-il)
NPL 9510 AIRFOIL - NPL 9510 transonic airfoil
| Details | Dat file | Parser | |
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(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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Polars for NPL 9510 AIRFOIL (npl9510-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| npl9510-il | 50,000 | 9 | 15.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 50,000 | 5 | 17 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 100,000 | 9 | 18.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 100,000 | 5 | 23.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 200,000 | 9 | 25.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 200,000 | 5 | 32.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 500,000 | 9 | 40.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 500,000 | 5 | 49.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9510-il | 1,000,000 | 9 | 57.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9510-il | 1,000,000 | 5 | 67.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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