NPL 9615 AIRFOIL (npl9615-il)
NPL 9615 AIRFOIL - NPL 9615 rotorcraft airfoil
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(npl9615-il) NPL 9615 AIRFOIL NPL 9615 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 9615 AIRFOIL
60. 46.
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
0.7650496 0.0329125
0.8180715 0.0271877
0.8590900 0.0212268
0.9061034 0.0148840
0.9530126 0.0082426
0.9765658 0.0048206
1.0000010 0.0001300
0.0000001 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
0.7642383 -.0264819
0.8173968 -.0222077
0.8585628 -.0173696
0.9057319 -.0123134
0.9528050 -.0069560
0.9764429 -.0041786
1.0000000 -.0001300
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Polars for NPL 9615 AIRFOIL (npl9615-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| npl9615-il | 50,000 | 9 | 29 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 5 | 30.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 9 | 43.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 5 | 42.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 9 | 56.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 9 | 70.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 5 | 68.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 9 | 84.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 5 | 77.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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