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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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At least 253 records · Page 14

All sources NASA NTRS DOE OSTI

NASA NTRS1952

Preliminary Investigation at Transonic Speeds of the Effect of Balancing Tabs on the Hinge-moment and Other Aerodynamic Characteristics of a Full-span Flap on a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3

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Lockwood, Vernard E↗

NASA NTRS1952

Control Characteristics at Transonic Speeds of a Linked Flap and Spoiler on a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3

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Lockwood, Vernard E↗

NASA NTRS1952

Hinge-moment and Other Aerodynamic Characteristics at Transonic Speeds of a Quarter-span Spoiler on a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3

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Fikes, Joseph E↗

NASA NTRS1952

Preliminary Investigation of Control Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Horn-balanced Full-span Control

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Lowry, John G↗

NASA NTRS1952

Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method

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Hammond, Alexander D↗

NASA NTRS1952

Chordwise pressure distribution at high subsonic speeds near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil sections and equipped with various spoiler ailerons

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Hammond, Alexander, D↗

NASA NTRS1952

Hinge-moment and control-effectiveness characteristics of an outboard flap with an overhang nose balance on a tapered 35 degree sweptback wing of aspect ratio 4 : transonic-bump method

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Thompson, Robert F↗

NASA NTRS1952

Low-speed lateral-control investigation of a flap-type spoiler aileron with and without a deflector and slot on a 6-percent-thick, tapered, 45 degree sweptback wing of aspect ratio 4

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Watson, James M↗

NASA NTRS1952

Investigation at Transonic Speeds of the Effect of a Positive-lift Balancing Tab on the Hinge-moment and Lift-characteristics of a Full-span Flap on a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3

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Lockwood, Vernard E↗

NASA NTRS1953

The effect at high subsonic speeds of a flap-type aileron on the chordwise pressure distribution near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil section

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Hammond, Alexander D↗

NASA NTRS1952

Aerodynamic characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a full-span flap type of control with overhang balance : transonic-bump method

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Lockwood, Vernard E↗

NASA NTRS1954

Flight Investigation of the Rolling Effectiveness of Fingered Semaphore Spoilers on a Tapered 45 Degree Sweptback Wing Between Mach Numbers 0.6 and 1.3

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Church, James D↗

NASA NTRS1954

Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab

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Hammond, Alexander D↗

NASA NTRS1953

Investigation of the effect of chordwise positioning and shape of an underwing nacelle on the high-speed aerodynamic characteristics of a 45 degree sweptback tapered-in-thickness-ratio wing of aspect ratio 6

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Silvers, H Norman↗

NASA NTRS1950

Theoretical lift and damping in roll of thin wings with arbitrary sweep and taper at supersonic speeds : supersonic leading and trailing edges

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WINGS, THIN - STABILITY↗

NASA NTRS1949

Summary of the theoretical lift, damping-in-roll, and center-of-pressure characteristics of various wing plan forms at supersonic speed

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WINGS - LEADING EDGES↗

NASA NTRS1942

A method of shear-lag analysis of box beams for axial stresses, shear stresses, and shear center

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STRESSED SKIN - BEAMS, BOX-BENDING↗

NASA NTRS1944

The Influence of the Aerodynamic Span Effect on the Magnitude of the Torsional-divergence Velocity and on the Shape of the Corresponding Deflection Mode

A procedure which takes into account the aerodynamic span effect is given for the determination of the torsional-divergence velocities of monoplanes. The explicit solutions obtained in several cases indicate that the aerodynamic span effect may increase the divergence velocities found by means of the section-force theory by as much as 17 to 40 percent. It is found that the magnitude of the effect increases with increasing degree of stiffness taper and decreases with increasing degree of chord taper. By a slight extension of the present method it is possible to analyze the elastic deformations of wings, and the resultant lift distributions, before torsional divergence occurs.

MONOPLANES↗