Static stability of fuselages having a relatively flat cross sections
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Bates, William R↗
SEARCH · Engineering Papers
Results for “Cross Section”
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Effects of certain flow nonuniformities on lift, drag, and pitching moment for a transonic-airplane model investigated at a Mach number of 1.2 in a nozzle of circular cross section
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Ritchie, Virgil S↗
Damping in Yaw and Static Directional Stability of a Canard Airplane Model and of Several Models Having Fuselages of Relatively Flat Cross Section
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Johnson, Joseph L↗
Some Effects of Body Cross-sectional Shape, Including Sunken-canopy Design, on Drag as Shown by Rocket-powered-model Tests at Mach Numbers from 0.8 to 1.5
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Stoney, William E , Jr↗
Free-flight-tunnel Investigation of the Low-speed Stability and Control Characteristics of a Model Having a Fuselage of Relatively Flat Cross Section
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Paulson, John W↗
Drag Measurements at Low Lift of a Four-nacelle Airplane Configuration Having a Longitudinal Distribution of Cross-sectional Area Conducive to Low Transonic Drag Rise
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Hopko, Russell N↗
Investigation of the Effects of Bomb-bay Configuration upon the Aerodynamic Characteristics of a Body with Circular Cross Section at Supersonic Speeds
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Rainey, Robert W↗
An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations
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Carlson, Harry W↗
Wind-tunnel Investigation at High Subsonic Speeds of Some Effects of Fuselage Cross-section Shape and Wing Height on the Static Longitudinal and Lateral Stability Characteristics of a Model Having a 45 Degree Swept Wing
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King, Thomas J , Jr↗
Some considerations of the influence of body cross-sectional shape on the lifting efficiency of wing-body combinations at supersonic speeds
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Klunker, E B↗
Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas
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Graves, Charles C↗
Investigation at Supersonic Speeds of the Effects of Bomb-bay Configuration upon the Aerodynamic Characteristics of Fuselages with Noncircular Cross Sections
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Rainey, Robert W↗
Investigation of static pressures and boundary-layer characteristics of the forward parts of nine fuselages of various cross-sectional shapes at M (sub infinity) equals 2.01
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Hasel, Lowell E↗
Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations
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Dryer, Murray↗
Theoretical and Experimental Analysis of Low-Drag Supersonic Inlets Having a Circular Cross Section and a Central Body at Mach Numbers 3.30, 2.75, and 2.45
Contains theoretical and experimental analysis of circular inlets having a central body at Mach numbers of 3.30, 2.75, and 2.45. The inlets have been designed in order to have low drag and high pressure recovery. The pressure recoveries obtained are of the same order of magnitude as those previously obtained by inlets having very large external drag.
Ferri, Antonio↗
A Theoretical and Experimental Study of Planing Surfaces Including Effects of Cross Section and Plan Form
A summary is given of the background and present status of the pure-planing theory for rectangular flat plates and v-bottom surfaces. The equations reviewed are compared with experiment. In order to extend the range of available planing data, the principal planing characteristics for models having sharp bottom surfaces having constant angles of dead rise of 20 degrees and 40 degrees. Planing data were also obtained for flat-plate surfaces with very slightly rounded chines for which decreased lift and drag coefficients are obtained.
Shuford, Charles L , Jr↗
An approximate method of shear-lag analysis for beams loaded at right angles to the plane of symmetry of the cross section
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STRESSED SKIN (LMAL)↗
Charts of Pressure, Density, and Temperature Changes at an Abrupt Increase in Cross-sectional Area of Flow of Compressible Air
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Joyner, Upshur T↗