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Evolution of the Airfoil, NASA history collection

Description The historical evolution of airfoil sections, 1908-1944. The last two shapes are low-drag sections designed to have laminar flow over 60 to 70 percent of chord on both the upper and lower surface... More

Evolution of the Airfoil, NASA history collection

The historical evolution of airfoil sections, 1908-1944. The last two shapes are low-drag sections designed to have laminar flow over 60 to 70 percent of chord on both the upper and lower surface...Image # : L-1990-04334

NACA Photographer Electrically heated airfoil - wing glove on C-46 airplane ARC-1946-A-10279

NACA Photographer Electrically heated airfoil - wing glove on C-46 airplane

DANLY AIRFOIL CUTTING MACHINE. ARC-1955-A-20618

DANLY AIRFOIL CUTTING MACHINE. Public domain photograph related to NASA research activity, space exploration, free to use, no copyright restrictions image - Picryl description

Interferogram of Transonic flow field - reconstructed laser hologram as an infinite-fringe interferogram shows shock-wave shape, location and separaton of the airfoil boundry layer ARC-1979-AC79-0054-1

Interferogram of Transonic flow field - reconstructed laser hologram as an infinite-fringe interferogram shows shock-wave shape, location and separaton of the airfoil boundry layer

Interferogram of Transonic flow field - reconstructed laser hologram as an infinite-fringe interferogram shows shock-wave shape, location and separaton of the airfoil boundry layer ARC-1979-A79-0054-4

Interferogram of Transonic flow field - reconstructed laser hologram as an infinite-fringe interferogram shows shock-wave shape, location and separaton of the airfoil boundry layer

A Clark Y Airfoil, mounted in the 40x80 foot wind tunnel.

Clark Y Airfoil. 3/4 front view of 8x48 foot Clark Y Airfoil mounted (inverted) in the 40x80 foot wind tunnel at NACA's Ames Research Center. Don Richey

N-231 High Reynolds Number Channel Facility (An example of a Versatile Wind Tunnel) Tunnel 1 I is a blowdown Facility that utilizes interchangeable test sections and nozzles. The facility provides experimental support for the fluid mechanics research, including experimental verification of aerodynamic computer codes and boundary-layer and airfoil studies that require high Reynolds number simulation. (Tunnel 1) ARC-1980-AC80-0512-2

N-231 High Reynolds Number Channel Facility (An example of a Versatile Wind Tunnel) Tunnel 1 I is a blowdown Facility that utilizes interchangeable test sections and nozzles. The facility provides experimental More

N-231 High Reynolds Number Channel Facility (Tunnel 2, Airfoil Test Section) ARC-1980-AC80-0512-1

N-231 High Reynolds Number Channel Facility (Tunnel 2, Airfoil Test Section)

N-231 High Reynolds Number Channel II Facility In this timeframe the test section was designed specifically to test two-dimensional airfoil models. It is equipped with 'through-the-wall' turntables that remotely position the airfoil, with flexible upper and lower walls that can be adjusted to minimize wall interference. Porous side-wall panels provide boundary-layer removal. ARC-1980-AC80-0512-3

N-231 High Reynolds Number Channel II Facility In this timeframe the test section was designed specifically to test two-dimensional airfoil models. It is equipped with 'through-the-wall' turntables that remote More