A study of the flow field behind the triangular horizontal tail of a canard airplane at approximately the vertical-tail location by means of a tuft grid
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Johnson, Joseph L , Jr↗
SEARCH · Engineering Papers
Results for “mean”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Effect of Magnitude of Vibratory Load Superimposed on Mean Tensile Load on Mechanism of and Time to Fracture of Specimens and Correlation to Engine Blade
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Ferguson, Robert R↗
A Free-flight Investigation at Zero Lift in the Mach Number Range Between 0.7 and 1.4 to Determine the Effectiveness of an Inset Tab as a Means of Aerodynamically Relieving Aileron Hinge Moments
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Bland, William M , Jr↗
An Investigation of a 0.16-scale Model of the Douglas X-3 Airplane to Determine Means of Improving the Low-speed Longitudinal Stability and Control Characteristics
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Mckee, John W↗
Investigation of Translating-spike Supersonic Inlet as Means of Mass-flow Control at Mach Numbers of 1.5, 1.8, and 2.0
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Gorton, Gerald C↗
Experimental Investigation of an Axial-flow Supersonic Compressor Having Rounded Leading-edge Blades with an 8-percent Mean Thickness-chord Ratio
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Goldberg, Theodore J↗
Performance comparison at supersonic speeds of inlets spilling excess flow by means of bow shock, conical shock, or bypass
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Allen, J L↗
A Preliminary Study by Means of Electrical Frequency-analysis Techniques of the Response of an Airplane Structure During Buffeting
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Yeates, John E , Jr↗
A correlation by means of transonic similarity rules of the experimentally determined characteristics of 18 cambered wings of rectangular plan form
The effects of one type of camber on the aerodynamic characteristics of rectangular wings at high subsonic and transonic speeds have been studied by applying the transonic similarity rules to the correlation of experimental data for a series of 18 cambered wings having NACA 63A2XX and 63A4XX sections, aspect ratios from 1 to 4, and thicknesses from 4 to 8 percent. The data were obtained by use of a transonic bump over a Mach number range of 0.6 to 1.1.
PROFILES - COMPLETE WINGS↗
Investigation of an Axial-flow Compressor Rotor Having NACA High-speed Blade Sections (a(sub 2)i(sub 8b) Series) at Mean Radius Relative Inlet Mach Numbers up to 1.13
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Savage, Melvyn↗
Low-velocity Turning as a Means of Minimizing Boundary-layer Accumulations Resulting from Secondary Flows Within Turbine Stators
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Stewart, Warner L↗
Subsonic flight investigation of methods to improve the damping of lateral oscillations by means of a viscous damper in the rudder system in conjunction with adjusted hinge-moment parameters
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Crane, Harold L↗
Two-dimensional low-speed cascade investigation of NACA compressor blade sections having a systematic variation in mean-line loading
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Erwin, John R↗
Experimental investigation of an axial-flow supersonic compressor having sharp leading-edge blades with an 8-percent mean thickness chord ratio
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Goldberg, Theodore J↗
Investigation of two short annular diffuser configurations utilizing section and injection as a means of boundary-layer control
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Wilbur, Langley W↗
Investigation of the Lateral Stability Characteristics of the Douglas X-3 Configuration at Mach Numbers from 0.6 to 1.1 by Means of a Rocket-propelled Model
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Mitchell, Jesse L↗
Experimental analysis of multicell wings by means of plastic models
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Zender, George W↗
Use of mean-section boundary-layer parameters in predicting three-dimensional turbine stator losses
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Stewart, Warner L↗
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