DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il)
DELFT DU84-132V3 AIRFOIL (MEASURED) - Airfoil measured from an ASW22 wing
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(du84132v-il) DELFT DU84-132V3 AIRFOIL (MEASURED) Airfoil measured from an ASW22 wing Max thickness 13.6% at 33.9% chord. Max camber 3.1% at 45.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DELFT DU84-132V3 AIRFOIL (MEASURED)
49. 49.
0.000000 0.000000
0.002280 0.010020
0.006830 0.017310
0.015950 0.026420
0.025060 0.033710
0.034170 0.039180
0.043280 0.044650
0.066060 0.054670
0.088840 0.062870
0.111620 0.070160
0.134400 0.075630
0.157180 0.081090
0.179950 0.085200
0.202730 0.088600
0.225510 0.091120
0.248290 0.092940
0.271070 0.094760
0.293850 0.095900
0.316630 0.096900
0.339410 0.097400
0.362190 0.097490
0.384970 0.097490
0.407740 0.097400
0.430520 0.096580
0.453300 0.095670
0.476080 0.093900
0.498860 0.092030
0.521640 0.090210
0.544420 0.088000
0.567200 0.085650
0.589980 0.083200
0.612760 0.080180
0.635540 0.077300
0.658310 0.073800
0.681090 0.070500
0.703870 0.066510
0.726650 0.062870
0.749430 0.058500
0.772210 0.054670
0.794990 0.050000
0.817770 0.045200
0.840550 0.040090
0.863330 0.035200
0.886100 0.030070
0.908880 0.024700
0.931660 0.019200
0.954440 0.013100
0.977220 0.006800
1.000000 0.000000
0.000000 0.000000
0.002280 -.005470
0.006830 -.011850
0.015950 -.016700
0.025060 -.020050
0.034170 -.022780
0.043280 -.024400
0.066060 -.028800
0.088840 -.031890
0.111620 -.034620
0.134400 -.036200
0.157180 -.037360
0.179950 -.038400
0.202730 -.039180
0.225510 -.039400
0.248290 -.039600
0.271070 -.039600
0.293850 -.039500
0.316630 -.039300
0.339410 -.038900
0.362190 -.038270
0.384970 -.037360
0.407740 -.036450
0.430520 -.035540
0.453300 -.034620
0.476080 -.033710
0.498860 -.032500
0.521640 -.031200
0.544420 -.030000
0.567200 -.028400
0.589980 -.026900
0.612760 -.025100
0.635540 -.022900
0.658310 -.020500
0.681090 -.017500
0.703870 -.014400
0.726650 -.010930
0.749430 -.007290
0.772210 -.003640
0.794990 0.000000
0.817770 0.002730
0.840550 0.004560
0.863330 0.005470
0.886100 0.005470
0.908880 0.005470
0.931660 0.004800
0.954440 0.003640
0.977220 0.001800
1.000000 0.000000
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Polars for DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| du84132v-il | 50,000 | 9 | 31.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 50,000 | 5 | 34.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 100,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 100,000 | 5 | 52.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 200,000 | 9 | 71.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 200,000 | 5 | 62.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 500,000 | 9 | 82 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 500,000 | 5 | 75.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 1,000,000 | 9 | 92.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 1,000,000 | 5 | 82.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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