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NPL 9660 AIRFOIL (npl9660-il)

NPL 9660 AIRFOIL - NPL 9660 rotorcraft airfoil


Airfoil npl9660-il
Details Dat file Parser  
(npl9660-il) NPL 9660 AIRFOIL
NPL 9660 rotorcraft airfoil
Max thickness 11.3% at 34.2% chord.
Max camber 1% at 19.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NPL 9660 AIRFOIL
       64.       50.

 0.0000000 0.0000000
 0.0045947 0.0120484
 0.0060458 0.0135887
 0.0087917 0.0162214
 0.0138628 0.0199625
 0.0175655 0.0223521
 0.0220616 0.0249910
 0.0262620 0.0272238
 0.0310540 0.0295685
 0.0364571 0.0319950
 0.0425612 0.0344818
 0.0495563 0.0370565
 0.0534946 0.0383828
 0.0577731 0.0397445
 0.0623921 0.0411315
 0.0674013 0.0425432
 0.0728709 0.0439787
 0.0789037 0.0456464
 0.0821512 0.0461921
 0.0855956 0.0472551
 0.0892321 0.0477255
 0.0931029 0.0485127
 0.0972338 0.0493163
 0.1016650 0.0501359
 0.1064364 0.0509708
 0.1114681 0.0518321
 0.1169403 0.0527175
 0.1231228 0.0536331
 0.1300259 0.0545988
 0.1376396 0.0555950
 0.1459735 0.0566112
 0.1548176 0.0576405
 0.1645814 0.0586572
 0.1750650 0.0596541
 0.1862682 0.0606211
 0.1981809 0.0615485
 0.2108029 0.0624262
 0.2244440 0.0632398
 0.2378717 0.0638065
 0.2518207 0.0644659
 0.2653884 0.0650307
 0.2842240 0.0654334
 0.3183978 0.0657166
 0.3417948 0.0654970
 0.3650891 0.0650788
 0.4123666 0.0634328
 0.4359513 0.0623106
 0.4829138 0.0595689
 0.5299682 0.0562258
 0.5770157 0.0523828
 0.6240577 0.0481398
 0.6709929 0.0433982
 0.7181240 0.0383539
 0.7782192 0.0314124
 0.8155617 0.0264719
 0.8538390 0.0211485
 0.8867293 0.0160487
 0.9158851 0.0113501
 0.9410564 0.0070558
 0.9619853 0.0033196
 0.9785000 0.0021939
 0.9904178 0.0020311
 0.9976141 0.0017628
 1.0000000 0.0012999

 0.0000000 0.0000000
 0.0001682 -.0023425
 0.0007393 -.0044505
 0.0018024 -.0071653
 0.0031720 -.0093842
 0.0054388 -.0118154
 0.0087123 -.0137603
 0.0127733 -.0166160
 0.0181401 -.0190396
 0.0233160 -.0208104
 0.0286979 -.0221341
 0.0350314 -.0233407
 0.0429623 -.0247392
 0.0494989 -.0257185
 0.0586313 -.0270034
 0.0719274 -.0287552
 0.0898772 -.0309706
 0.1001108 -.0321705
 0.1105250 -.0333229
 0.1313354 -.0354973
 0.1521776 -.0375322
 0.1730126 -.0393570
 0.1938801 -.0410121
 0.2147399 -.0424873
 0.2356422 -.0437829
 0.2565371 -.0448884
 0.2774345 -.0458139
 0.2983541 -.0465697
 0.3192567 -.0471053
 0.3402515 -.0474921
 0.3635486 -.0477104
 0.4108533 -.0473566
 0.4344599 -.0468790
 0.4814798 -.0454211
 0.5286079 -.0433647
 0.5757428 -.0408084
 0.6228831 -.0378520
 0.6699303 -.0343944
 0.7171816 -.0306395
 0.7774440 -.0253422
 0.8149074 -.0214236
 0.8533159 -.0171479
 0.8863333 -.0129485
 0.9156065 -.0090480
 0.9408857 -.0054430
 0.9619089 -.0022799
 0.9784482 -.0016057
 0.9903659 -.0017686
 0.9975669 -.0016969
 1.0000000 -.0012999
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Lednicer format dat file
Selig format dat file

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Polars for NPL 9660 AIRFOIL (npl9660-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   npl9660-il50,000928 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9660-il50,000530.1 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   npl9660-il100,000941.9 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9660-il100,000541.1 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   npl9660-il200,000954.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9660-il200,000551.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   npl9660-il500,000969.7 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9660-il500,000566.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   npl9660-il1,000,000981.5 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   npl9660-il1,000,000575.2 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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