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Supermarine 371-I (root) (supermarine371i-il)

Supermarine 371-I (root) - Supermarine 371-I root airfoil


Airfoil supermarine371i-il
Details Dat file Parser  
(supermarine371i-il) Supermarine 371-I (root)
Supermarine 371-I root airfoil
Max thickness 13% at 40% chord.
Max camber 0.9% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
Supermarine 371-I (root)
1.00	0.0000
0.95	0.0064
0.90	0.0142
0.85	0.0230
0.80	0.0323
0.75	0.0417
0.70	0.0507
0.65	0.0589
0.60	0.0657
0.55	0.0703
0.50	0.0728
0.45	0.0740
0.40	0.0741
0.35	0.0730
0.30	0.0708
0.25	0.0674
0.20	0.0625
0.15	0.0559
0.10	0.0468
0.075	0.0410
0.050	0.0337
0.025	0.0238
0.010	0.0149
0.005	0.0105
0.000	0.0000
0.005	-0.0097
0.010	-0.0135
0.025	-0.0207
0.050	-0.0284
0.075	-0.0349
0.100	-0.0380
0.15	-0.0444
0.20	-0.0490
0.25	-0.0522
0.30	-0.0543
0.35	-0.0556
0.40	-0.0559
0.45	-0.0555
0.5	-0.0542
0.55	-0.0519
0.60	-0.0489
0.65	-0.0431
0.70	-0.0368
0.75	-0.0299
0.80	-0.0229
0.85	-0.0161
0.90	-0.0098
0.95	-0.0044
1.00	 0.0000
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Lednicer format dat file
Selig format dat file

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Polars for Supermarine 371-I (root) (supermarine371i-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   supermarine371i-il50,000928.6 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371i-il50,000527.6 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   supermarine371i-il100,000946.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371i-il100,000541 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   supermarine371i-il200,000957.9 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371i-il200,000552.2 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   supermarine371i-il500,000978.5 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371i-il500,000564 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   supermarine371i-il1,000,000989.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371i-il1,000,000566.4 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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