Search results
Results From The WOW.Com Content Network
For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.
NACA experience provided a model for World War II research, the postwar government laboratories, and NACA's successor, the National Aeronautics and Space Administration (NASA). NACA also participated in development of the first aircraft to fly to the "edge of space", North American's X-15. NACA airfoils are still used on modern aircraft.
The Ferrari F40 sports car has "NACA style" side and hood scoops.. It is especially favored in racing car design. [4] [5] Sports cars featuring prominent NACA ducts include the Ferrari F40, the Lamborghini Countach, the 1996–2002 Dodge Viper, the 1971–1973 Ford Mustang, the 1973 Pontiac GTO, the 1979 Porsche 924 Turbo, the Maserati Biturbo, the Nissan S130, and the Porsche 911 GT2.
In aerodynamics, the lift-to-drag ratio (or L/D ratio) is the lift generated by an aerodynamic body such as an aerofoil or aircraft, divided by the aerodynamic drag caused by moving through air. It describes the aerodynamic efficiency under given flight conditions. The L/D ratio for any given body will vary according to these flight conditions.
From Kirkup, Jones learned about airplane design and stress analysis. [1] Jones developed the Pobjoy Special air racer, but because of the depression the company was forced to shut down. [3] With the help of his local congressman, Jones found work as an elevator operator in the House Office Building in Washington, D.C.
In February 1976, work commenced to automate the methods contained in the USAF Stability and Control DATCOM, specifically those contained in sections 4, 5, 6 and 7.The work was performed by the McDonnell Douglas Corporation under contract with the United States Air Force in conjunction with engineers at the Air Force Flight Dynamics Laboratory in Wright-Patterson Air Force Base.
a=chord, b=thickness, thickness-to-chord ratio = b/a The F-104 wing has a very low thickness-to-chord ratio of 3.36%. In aeronautics, the thickness-to-chord ratio, sometimes simply chord ratio or thickness ratio, compares the maximum vertical thickness of a wing to its chord.
Clark Y is the name of a particular airfoil profile, widely used in general purpose aircraft designs, and much studied in aerodynamics over the years. The profile was designed in 1922 by Virginius E. Clark using thickness distribution of the German-developed Goettingen 398 airfoil. [1]