A general solution for minimum impulse transfers in the near vicinity of a circular orbit
Analytic solution for minumum impulse transfer between two neighboring low eccentricity orbits
CIRCULAR ORBIT↗
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Results for “circular”
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Minimum impulse transfers in the near vicinity of a circular orbit.
Analytic solution obtained for minimum impulse transfer between two neighboring low eccentricity orbits
THRUST CONTROL↗
Attitude instability regions of a spinning unsymmetrical satellite in a circular orbit.
Attitude continuous instability regions in parameter space and resonance frequency of spinning unsymmetrical satellite noting periodic processes
PERIODIC FUNCTION↗
Jet-boundary and Plan-form Corrections for Partial-span Models with Reflection Plane, End Plate, or No End Plate in a Closed Circular Wind Tunnel
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WIND TUNNEL TESTS - NACA PRESSURE (19')↗
An Investigation of Aircraft Heaters XXVII : Distribution of Heat-transfer Rate in the Entrance Section of a Circular Tube
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AIR FLOW - PIPES - TURBULENT↗
Experimental investigation of the jet-boundary constriction correction for a model spanning a closed circular tunnel
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WIND TUNNEL WALL INTERFERENCE, CIRCULAR↗
Reinforced Circular Cutouts in Plane Sheets
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PLATES - BENDING↗
Turning-angle design rules for constant-thickness circular-arc inlet guide vanes in axial annular flow
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COMPRESSORS, AXIAL↗
An Approximate Method of Calculating Pressures in the Tip Region of a Rectangular Wing of Circular-Arc Section at Supersonic Speeds
No abstract available
PRESSURE DISTRIBUTION - WING TIPS↗
Normal-pressure Tests of Circular Plates with Clamped Edges
A fixture is described for making normal-pressure tests of flat plates 5 inches in diameter in which particular care was taken to obtain rigid clamping at the edges. Results are given for 19 plates, ranging in thickness from 0.015 to 0.072 inch. The center deflections and the extreme-fiber stresses at low pressures were found to agree with theoretical values; the center deflections at high pressures were 4 to 12 percent greater than the theoretical values. Empirical curves are derived of the pressure for the beginning of permanent set as a function of the dimensions of the plate and the tensile properties of the material.
CIRCULAR↗
Investigation of Effect of Sideslip on Lateral Stability Characteristics II : Rectangular Midwing on Circular Fuselage with Variations in Vertical-tail Area and Fuselage Length with and Without Horizontal Tail Surface
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TAIL SURFACES, HORIZONTAL↗
Investigation of Effect of Sideslip on Lateral Stability Characteristics III : Rectangular Low Wing on Circular Fuselage with Variations in Vertical-tail Area and Fuselage Length With and Without Horizontal Tail Surface
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MONOPLANES, LOW-WING↗
Investigation of Effect of Sideslip on Lateral Stability Characteristics I : Circular Fuselage with Variations in Vertical-Tail Area and Tail Length with and Without Horizontal Tail Surface
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TAIL SURFACES - AREA↗
Wind tunnel investigation of effect of yaw on lateral-stability characteristics IV : symmetrically tapered wing with a circular fuselage having a wedge-shaped rear and a vertical tail
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MONOPLANES, MID-WING VS HIGH- & LOW-WING↗
Wind-tunnel investigation of effect of yaw on lateral-stability characteristics V : symmetrically tapered wing with a circular fuselage having a horizontal and a vertical tail
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WING FLAPS, SPLIT - PARTIAL-SPAN (20%-CHORD)↗
The effect of wall interference upon the aerodynamic characteristics of an airfoil spanning a closed-throat circular wind tunnel
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AIRFOILS - NACA - LOW-DRAG↗
Strength Tests of Thin-wall Truncated Cones of Circular Section
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CYLINDERS, CIRCULAR - STRENGTH↗
A multi-layer circularly polarized microstrip patch antenna with proximity coupling and increased gain
Presented is a description of the single stacked element, and measured and calculated results at 2.56 GHz. Also included are measured results for the array, and calculated results of a stacked element for the required frequency-scaled version at 32 GHz.
gain microstrip patch antenna mulit-layered stacke↗