NPL 9660 AIRFOIL (npl9660-il)
NPL 9660 AIRFOIL - NPL 9660 rotorcraft airfoil
| Details | Dat file | Parser | |
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(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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Polars for NPL 9660 AIRFOIL (npl9660-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| npl9660-il | 50,000 | 9 | 28 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 50,000 | 5 | 30.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 100,000 | 9 | 41.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 100,000 | 5 | 41.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 200,000 | 9 | 54.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 200,000 | 5 | 51.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 500,000 | 9 | 69.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 500,000 | 5 | 66.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 1,000,000 | 9 | 81.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 1,000,000 | 5 | 75.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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