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NACA 0012 with modifications?
$9.3 to $15 million
Naca
It's about 13.5 - 14 mn dollars.
Airfoil of Supersonigjetwing
Approximately $14 Million new. used up to 4 years old, is about $11.5 Million
In 1939, Eastman Jacobs at the NACA in Langley, designed and tested the first laminar flow airfoil sections. These shapes had extremely low drag and the section shown here achieved a lift to drag ratio of about 300.
Modern airplanes have swept wings and so the NACA airfoil system is hard to apply since it it is constantly changing throughout the wing. Even if it was still in use, or another system is in use, the fact is that most companies keep these values extremely confidential since the wing is the most important part of a plane and they dont want other companies copying their airplanes.
min lift coeff of 1412 =.60 thefore Cl will be 1.10 at angle of attatck 4 and mach .8
Kenneth D. Korkan has written: 'Experimental study of performance degradation of a rotating system in the NASA Lewis RC icing tunnel' -- subject(s): Ice prevention, Rotors (Helicopters), Airplanes 'Aerodynamic data banks for Clark-Y, NACA 4-digit, and NACA 16-series airfoil families'
Philip E. Poinsatte has written: 'Heat transfer measurements from a NACA 0012 airfoil in flight and in the NASA Lewis Icing Research Tunnel' -- subject(s): Transmission, Heat, Aerofoils, Measurement
Gulfstream Aerospace was created in 1978.