GOE 142 (MVA H.19) AIRFOIL (goe142-il)
GOE 142 (MVA H.19) AIRFOIL - Gottingen 142 (MVA H.19) airfoil
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(goe142-il) GOE 142 (MVA H.19) AIRFOIL Gottingen 142 (MVA H.19) airfoil Max thickness 6.2% at 24.9% chord. Max camber 3.8% at 34.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 142 (MVA H.19) AIRFOIL
50. 50.
0.0000000 0.0000000
0.0004800 0.0026500
0.0009600 0.0038500
0.0014600 0.0047900
0.0019500 0.0056100
0.0024400 0.0063400
0.0029400 0.0070200
0.0039200 0.0082500
0.0049100 0.0093600
0.0073900 0.0118100
0.0098700 0.0139500
0.0123500 0.0158800
0.0148400 0.0176700
0.0198100 0.0209500
0.0247800 0.0238900
0.0347300 0.0290900
0.0496700 0.0356600
0.0746000 0.0443300
0.0995400 0.0508900
0.1244900 0.0559000
0.1494500 0.0597700
0.1744300 0.0627300
0.1994100 0.0649600
0.2243900 0.0666000
0.2493800 0.0677400
0.2743800 0.0684400
0.2993700 0.0687600
0.3493700 0.0684600
0.3993900 0.0670900
0.4494100 0.0648400
0.4994400 0.0618300
0.5494700 0.0581400
0.5995100 0.0538300
0.6495500 0.0489500
0.6745800 0.0463000
0.6996000 0.0435200
0.7246300 0.0406000
0.7496600 0.0375600
0.7746900 0.0343900
0.7997200 0.0310900
0.8247500 0.0276700
0.8497800 0.0241200
0.8748100 0.0204700
0.8998500 0.0167200
0.9248800 0.0128700
0.9499199 0.0089500
0.9699500 0.0057800
0.9799600 0.0041900
0.9899800 0.0026000
1.0000000 0.0010000
0.0000000 0.0000000
0.0005200 -.0023600
0.0010300 -.0032400
0.0015400 -.0038800
0.0020400 -.0043900
0.0025400 -.0048300
0.0030500 -.0052000
0.0040500 -.0058300
0.0050600 -.0063400
0.0075700 -.0072900
0.0100700 -.0079600
0.0125800 -.0084500
0.0150800 -.0088000
0.0200800 -.0092300
0.0250900 -.0093900
0.0350800 -.0092300
0.0500800 -.0083200
0.0750600 -.0060600
0.1000300 -.0036600
0.1250100 -.0014000
0.1499900 0.0006100
0.1749800 0.0023500
0.1999600 0.0038400
0.2249500 0.0050900
0.2499400 0.0061300
0.2749400 0.0069800
0.2999300 0.0076500
0.3499200 0.0085300
0.3999200 0.0089000
0.4499200 0.0089000
0.4999200 0.0086300
0.5499300 0.0082100
0.5999300 0.0076400
0.6499400 0.0069300
0.6749400 0.0065300
0.6999400 0.0060900
0.7249500 0.0056200
0.7499501 0.0051100
0.7749600 0.0045800
0.7999600 0.0040300
0.8249700 0.0034500
0.8499700 0.0028500
0.8749800 0.0022300
0.8999900 0.0016000
0.9249900 0.0009600
0.9500000 0.0003100
0.9700000 -.0002100
0.9800000 -.0004700
0.9900100 -.0007400
1.0000000 -.0010000
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Polars for GOE 142 (MVA H.19) AIRFOIL (goe142-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe142-il | 50,000 | 9 | 36.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 50,000 | 5 | 41 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 100,000 | 9 | 55.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 100,000 | 5 | 56.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 200,000 | 9 | 74.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 200,000 | 5 | 72.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 500,000 | 9 | 99 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 500,000 | 5 | 94.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 1,000,000 | 9 | 118.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 1,000,000 | 5 | 111.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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