NPL 9627 AIRFOIL (npl9627-il)
NPL 9627 AIRFOIL - NPL 9627 rotorcraft airfoil
| Details | Dat file | Parser | |
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(npl9627-il) NPL 9627 AIRFOIL NPL 9627 rotorcraft airfoil Max thickness 12.2% at 31% chord. Max camber 0.9% at 40.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NPL 9627 AIRFOIL
42. 42.
0.0000000 0.0000000
0.0002476 0.0029864
0.0005754 0.0047214
0.0011059 0.0066331
0.0017332 0.0083333
0.0025718 0.0101301
0.0036927 0.0120524
0.0052333 0.0145981
0.0067636 0.0164939
0.0082926 0.0182996
0.0099297 0.0199937
0.0153953 0.0247168
0.0219940 0.0290118
0.0386552 0.0372163
0.0597401 0.0437697
0.0850717 0.0501252
0.1143857 0.0559969
0.1474242 0.0608989
0.1838366 0.0647967
0.2232891 0.0674558
0.2654048 0.0690622
0.3097725 0.0695423
0.3559633 0.0689732
0.4035249 0.0671920
0.4520221 0.0645157
0.5009748 0.0609321
0.5499189 0.0568085
0.5983862 0.0522624
0.6458989 0.0474316
0.6920185 0.0424031
0.7362969 0.0373040
0.7783054 0.0322112
0.8176356 0.0272213
0.8539093 0.0224503
0.8867972 0.0179535
0.9159516 0.0138465
0.9411231 0.0101933
0.9620534 0.0070880
0.9785434 0.0045839
0.9904341 0.0027534
0.9976162 0.0016383
1.0000000 0.0012598
0.0000000 0.0000000
0.0001611 -.0024229
0.0004386 -.0038275
0.0009137 -.0053853
0.0014920 -.0067447
0.0022793 -.0081575
0.0033475 -.0095248
0.0048239 -.0109986
0.0063003 -.0124724
0.0077807 -.0136962
0.0093744 -.0147219
0.0147116 -.0180177
0.0211957 -.0208918
0.0376337 -.0266355
0.0585189 -.0325605
0.0836598 -.0381334
0.1128039 -.0428803
0.1457030 -.0466872
0.1820076 -.0495283
0.2213881 -.0513687
0.2634646 -.0522120
0.3078271 -.0520618
0.3540439 -.0510111
0.4016632 -.0491828
0.4502347 -.0472097
0.4992811 -.0449342
0.5483320 -.0423787
0.5969200 -.0393857
0.6445629 -.0360775
0.6908197 -.0325272
0.7352386 -.0288475
0.7773885 -.0251014
0.8168581 -.0213724
0.8532659 -.0177645
0.8862809 -.0143223
0.9155517 -.0111502
0.9408271 -.0083043
0.9618461 -.0058703
0.9784077 -.0038950
0.9903509 -.0024459
0.9975650 -.0015612
1.0000000 -.0012598
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Polars for NPL 9627 AIRFOIL (npl9627-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| npl9627-il | 50,000 | 9 | 28.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9627-il | 50,000 | 5 | 29.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9627-il | 100,000 | 9 | 42.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9627-il | 100,000 | 5 | 40.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9627-il | 200,000 | 9 | 54.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9627-il | 200,000 | 5 | 49 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9627-il | 500,000 | 9 | 66.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9627-il | 500,000 | 5 | 64.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9627-il | 1,000,000 | 9 | 80.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9627-il | 1,000,000 | 5 | 81.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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