Many experimental arrangements of varying kind involve the problems of assuring a large, steady air stream both as to volume and to time. For this reason a separate discussion of the methods by which this is achieved should prove of particular interest. Motors and blades receive special attention and a review of existent wind tunnels is also provided
Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynol...
This paper is one of several dealing with methods intended to reduce the drag of present-day radial ...
With the assistance and cooperation of the National Advisory Committee for Aeronautics the Bureau of...
Based on theoretical studies and experience with a low speed cryogenic tunnel and with a 1/3-meter t...
The most important aerodynamical qualities that should be aimed at in wind tunnel design, are as fol...
Many experimental arrangements of varying kind involve the problems of assuring a large, steady air ...
Now, in existing wind tunnels, using a horsepower of 100 to 300, the models are generally made to a ...
A wind tunnel investigation was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel to stu...
The use of exit cones and different blade configurations to reduce the motive power required in wind...
This report is a continuation of National Advisory Committee for Aeronautics report no. 73. The vari...
The NASA Lewis 1x1 foot supersonic wind tunnel is used to experimentally verify computational method...
A wind tunnel for testing model airplanes and their parts requires accurate control of the air veloc...
The paper suggests a simple method o f13; generating intermittent reservoir conditions for an13; int...
This report discusses the general considerations for the design of aerodynamic laboratories. The dim...
Computations of drag polars for a low-speed Wortmann sailplane airfoil are compared to both wind tun...
Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynol...
This paper is one of several dealing with methods intended to reduce the drag of present-day radial ...
With the assistance and cooperation of the National Advisory Committee for Aeronautics the Bureau of...
Based on theoretical studies and experience with a low speed cryogenic tunnel and with a 1/3-meter t...
The most important aerodynamical qualities that should be aimed at in wind tunnel design, are as fol...
Many experimental arrangements of varying kind involve the problems of assuring a large, steady air ...
Now, in existing wind tunnels, using a horsepower of 100 to 300, the models are generally made to a ...
A wind tunnel investigation was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel to stu...
The use of exit cones and different blade configurations to reduce the motive power required in wind...
This report is a continuation of National Advisory Committee for Aeronautics report no. 73. The vari...
The NASA Lewis 1x1 foot supersonic wind tunnel is used to experimentally verify computational method...
A wind tunnel for testing model airplanes and their parts requires accurate control of the air veloc...
The paper suggests a simple method o f13; generating intermittent reservoir conditions for an13; int...
This report discusses the general considerations for the design of aerodynamic laboratories. The dim...
Computations of drag polars for a low-speed Wortmann sailplane airfoil are compared to both wind tun...
Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynol...
This paper is one of several dealing with methods intended to reduce the drag of present-day radial ...
With the assistance and cooperation of the National Advisory Committee for Aeronautics the Bureau of...