PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il)
PROPFAN CRUISE MISSILE WING AIRFOIL - Propfan Cruise Missile wing airfoil
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(pfcm-il) PROPFAN CRUISE MISSILE WING AIRFOIL Propfan Cruise Missile wing airfoil Max thickness 8.2% at 40% chord. Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
PROPFAN CRUISE MISSILE WING AIRFOIL
26. 26.
0.000000 0.000000
0.005000 0.007560
0.007500 0.009110
0.012500 0.011580
0.025000 0.016230
0.050000 0.022900
0.075000 0.028040
0.100000 0.032340
0.150000 0.039180
0.200000 0.044410
0.250000 0.048330
0.300000 0.051170
0.350000 0.052990
0.400000 0.053750
0.450000 0.053270
0.500000 0.051710
0.550000 0.049250
0.600000 0.046000
0.650000 0.042070
0.700000 0.037510
0.750000 0.032440
0.800000 0.026940
0.850000 0.020750
0.900000 0.014370
0.950000 0.007840
1.000000 0.001310
0.000000 0.000000
0.005000 -0.005700
0.007500 -0.006840
0.012500 -0.008570
0.025000 -0.011520
0.050000 -0.015320
0.075000 -0.018010
0.100000 -0.020160
0.150000 -0.023390
0.200000 -0.025680
0.250000 -0.027230
0.300000 -0.028160
0.350000 -0.028490
0.400000 -0.028180
0.450000 -0.026990
0.500000 -0.025110
0.550000 -0.022710
0.600000 -0.019940
0.650000 -0.016920
0.700000 -0.013780
0.750000 -0.010750
0.800000 -0.008140
0.850000 -0.006220
0.900000 -0.004480
0.950000 -0.002890
1.000000 -0.001300
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Polars for PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pfcm-il | 50,000 | 9 | 30.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 50,000 | 5 | 33 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pfcm-il | 100,000 | 9 | 47 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 100,000 | 5 | 44.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pfcm-il | 200,000 | 9 | 61.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 200,000 | 5 | 56.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pfcm-il | 500,000 | 5 | 67.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pfcm-il | 500,000 | 0 | 78.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 1,000,000 | 9 | 88.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 1,000,000 | 5 | 70.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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