GIII BL332 AIRFOIL (giiij-il)
GIII BL332 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils
| Details | Dat file | Parser | |
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(giiij-il) GIII BL332 AIRFOIL Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35% chord. Max camber 1.4% at 25% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GIII BL332 AIRFOIL
26. 26.
0.0000000 0.0000000
0.0050001 0.0110500
0.0075001 0.0133299
0.0125002 0.0167999
0.0250002 0.0229197
0.0500003 0.0308695
0.0750004 0.0364392
0.1000004 0.0408590
0.1500005 0.0472985
0.2000005 0.0515580
0.2500005 0.0541775
0.3000006 0.0555470
0.3500006 0.0557765
0.4000006 0.0550360
0.4500005 0.0532755
0.5000006 0.0510850
0.5500005 0.0482645
0.6000005 0.0446440
0.6500004 0.0402635
0.7000004 0.0353530
0.7500003 0.0300325
0.8000003 0.0243620
0.8500002 0.0183115
0.9000001 0.0122710
0.9500001 0.0062205
1.0000000 0.0001800
0.0000000 0.0000000
0.0049999 -.0080101
0.0074999 -.0094701
0.0124999 -.0114301
0.0249999 -.0136403
0.0499998 -.0159605
0.0749998 -.0179308
0.0999998 -.0195910
0.1499998 -.0222915
0.1999998 -.0244720
0.2499997 -.0262825
0.2999997 -.0279130
0.3499997 -.0290835
0.3999997 -.0298240
0.4499997 -.0299745
0.4999997 -.0295350
0.5499997 -.0284755
0.5999998 -.0267660
0.6499998 -.0245065
0.6999998 -.0215270
0.7499998 -.0179975
0.7999998 -.0144380
0.8499999 -.0108685
0.8999999 -.0073090
0.9499999 -.0037495
1.0000000 -.0001800
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Polars for GIII BL332 AIRFOIL (giiij-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiij-il | 50,000 | 9 | 32.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 50,000 | 5 | 32.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 100,000 | 9 | 46.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 100,000 | 5 | 43.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 200,000 | 9 | 59.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 200,000 | 5 | 52.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 500,000 | 9 | 73.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 500,000 | 5 | 65.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 1,000,000 | 9 | 79.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 1,000,000 | 5 | 79.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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