NACA
National Advisory Committee for Aeronautics, NASA's predecessor, 1915 to 1958.
Search for NACA books on Amazon.co.uk ...
NACA: The National Advisory Committee for Aeronautics in the United States of America - a body specially concerned with research and experiment (superseded by NASA - National Aeronautics & Space Administration - in 1958).
NACA, the precursor to the United States' NASA, researched the advantages of forward-swept wings on the Bell X-1, but encountered structural problems with twisting wingtips.
Described in NACA-TN-259, of August 1927, as "a new corrosion resistant aluminum product which is markedly superior to the present strong alloys. Its use should result in greatly increased life of a structural part.
Prior to 1958, USAF and NACA (later NASA) officials discussed an orbital X-15, called the "X-15B", to be launched into space atop a Navajo missile.
NACA 4412, NACA 22012 and NACA 23012 or 23015). All of these airfoils are relatively insensitive to roughness (dirt or manufacturing imperfection) on the leading edge and except for the 4412 or 4415, ...
Airfoil: NACA 64A 05.92 root, NACA 64A 04.29 tip
Empty weight: 43,430 lb (19,700 kg
Loaded weight: 64,460 lb (29,300 kg)
Max takeoff weight: 83,500 lb (38,000 kg) ...
However, wartime NACA research data I have shows that Mustangs were not manufactured with a sufficient degree of surface quality to maintain much laminar flow on the wing.
The NACA 2412 airfoil is optimized more for climb than cruise, but the airplane will still generate about 125 knots if the CG is full aft, vents are closed, prop and engine are working at optimum, ...
28, which shows wind-tunnel data for a real airfoil (the NACA 631-412 airfoil; see reference 24). At cruise angle of attack, the drag is approximately doubled; at higher angles of attack (corresponding to lower airspeeds) it is even worse.
Calculate the lift curve slope for a NACA 23012 wing of 2-D lift curve slope = 0.106 per degree, aspect ratio = 10, Re = 5 x 106 and span effectiveness factor = 0.95.
Solution:
a = ao / [(1 + 57.3 ao) / (π e A)] = 0.088 per degree ...
 See also: Aircraft, Plane, Aviation, Speed, Force
  
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