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Supermarine 371-II (tip) (supermarine371ii-il)

Supermarine 371-II (tip) - Supermarine 371-II tip airfoil


Airfoil supermarine371ii-il
Details Dat file Parser  
(supermarine371ii-il) Supermarine 371-II (tip)
Supermarine 371-II tip airfoil
Max thickness 8.4% at 50% chord.
Max camber 0.9% at 45% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
Supermarine 371-II (tip)
1.00	0.0000
0.95	0.0044
0.90	0.0101
0.85	0.0168
0.80	0.0236
0.75	0.0305
0.70	0.0372
0.65	0.0430
0.60	0.0476
0.55	0.0501
0.50	0.0511
0.45	0.0510
0.40	0.0500
0.35	0.0482
0.30	0.0456
0.25	0.0424
0.20	0.0382
0.15	0.0331
0.10	0.0269
0.075	0.0230
0.050	0.0185
0.025	0.0127
0.010	0.0079
0.005	0.0055
0.000	0.0000
0.005	-0.0046
0.010	-0.0064
0.025	-0.0098
0.050	-0.0134
0.075	-0.0160
0.100	-0.0183
0.15	-0.0218
0.20	-0.0248
0.25	-0.0271
0.30	-0.0291
0.35	-0.0306
0.40	-0.0318
0.45	-0.0324
0.5	-0.0325
0.55	-0.0319
0.60	-0.0304
0.65	-0.0273
0.70	-0.0232
0.75	-0.0196
0.80	-0.0142
0.85	-0.0099
0.90	-0.0058
0.95	-0.0024
1.00	 0.0000
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Lednicer format dat file
Selig format dat file

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Polars for Supermarine 371-II (tip) (supermarine371ii-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   supermarine371ii-il50,000919.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371ii-il50,000523.1 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   supermarine371ii-il100,000929.9 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371ii-il100,000537.5 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   supermarine371ii-il200,000951.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371ii-il200,000545.7 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   supermarine371ii-il500,000963.7 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371ii-il500,000554.3 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   supermarine371ii-il1,000,000973.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   supermarine371ii-il1,000,000558.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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