NPL AIRFOIL FROM ARC CP 1372 (nplx-il)
NPL AIRFOIL FROM ARC CP 1372 - NPL transonic airfoil FROM ARC CP 1372
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(nplx-il) NPL AIRFOIL FROM ARC CP 1372 NPL transonic airfoil FROM ARC CP 1372 Max thickness 10.7% at 35.8% chord. Max camber 1.1% at 73.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NPL AIRFOIL FROM ARC CP 1372
34. 34.
0.000000 -0.010150
0.001000 -0.004300
0.002990 0.001220
0.004980 0.004110
0.007360 0.006760
0.014540 0.012000
0.026420 0.016870
0.042840 0.021490
0.063730 0.025730
0.088810 0.029810
0.117910 0.033980
0.150700 0.037930
0.186870 0.041400
0.226070 0.044170
0.267960 0.046180
0.312090 0.047620
0.358060 0.048700
0.405420 0.049130
0.453730 0.049250
0.502490 0.048730
0.551240 0.047400
0.599550 0.045550
0.646920 0.042770
0.692890 0.039090
0.737020 0.034890
0.778910 0.030510
0.818110 0.026220
0.854280 0.022080
0.887070 0.017910
0.900000 0.016200
0.911870 0.014640
0.937050 0.011130
0.968520 0.006160
1.000000 0.000000
0.000000 -0.010150
0.001000 -0.015060
0.002990 -0.018410
0.004980 -0.020120
0.007360 -0.021900
0.014540 -0.025810
0.026420 -0.029950
0.042840 -0.033870
0.063730 -0.037570
0.088810 -0.040800
0.117910 -0.044130
0.150700 -0.047130
0.186870 -0.049910
0.226070 -0.052910
0.267960 -0.055660
0.312090 -0.057320
0.358060 -0.057960
0.405420 -0.057010
0.453730 -0.054030
0.502490 -0.049320
0.551240 -0.043630
0.599550 -0.037340
0.646920 -0.030880
0.692890 -0.024600
0.737020 -0.018700
0.778910 -0.013650
0.818110 -0.009350
0.854280 -0.005900
0.887070 -0.003250
0.900000 -0.002450
0.911870 -0.001560
0.937050 -0.000430
0.968520 0.000260
1.000000 0.000000
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Polars for NPL AIRFOIL FROM ARC CP 1372 (nplx-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nplx-il | 50,000 | 9 | 22 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 50,000 | 5 | 22.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 100,000 | 9 | 28.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 100,000 | 5 | 28.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 200,000 | 9 | 41 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 200,000 | 5 | 38.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 500,000 | 9 | 49.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 500,000 | 5 | 54.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 1,000,000 | 9 | 62.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 1,000,000 | 5 | 70.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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