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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 55 records · Page 3

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NASA NTRS1957

Dynamic Stability Investigation of Two Right Circular Cylinders in Axial Free Flight at Mach Numbers from 0.4 to 1.7 Fineness-ratio-2.56 Cylinder and Fineness-ratio-4.0 Cylinder with Flared Afterbody

Dynamic longitudinal stability of right circular cylinders in axial free flight

CIRCULAR CYLINDER↗

NASA NTRS1954

The Zero-lift Drag of a 60 Degree Delta-wing-body Combination (AGARD Model 2) Obtained from Free-flight Tests Between Mach Numbers of 0.8 and 1.7

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Piland, Robert O↗

NASA NTRS1950

Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift

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Morrow, John D↗

NASA NTRS1950

Experimental determination of effect of structural rigidity on rolling effectiveness of some straight and swept wings at Mach numbers from 0.7 to 1.7

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Strass, H Kurt↗

NASA NTRS1950

Comparison of large scale flight measurements of zero lift drag at Mach numbers from 0.9 to 1.7 of two wing-body combinations having similar 60 degree triangular wings with NACA 65A003 sections

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Schult, Eugene D↗

NASA NTRS1951

Preliminary Data on the Effect of Body-nose Bluntness on the Drag and Pressure Recovery of a Side-inlet-body Combination at Mach Numbers of 1.4 and 1.7

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Stroud, John F↗

NASA NTRS1951

Flight Determination of Drag and Pressure Recovery of a Nose Inlet of Parabolic Profile at Mach Numbers from 0.8 to 1.7

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Sears, Richard I↗

NASA NTRS1952

Experimental Investigation of the Effect of Forebody Bluntness on the Pressure Recovery and Drag of a Twin-scoop Inlet-body Combination at Mach Numbers of 1.4 and 1.7

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Stroud, John F↗

NASA NTRS1952

Some Effects of Spoiler Height, Wing Flexibility, and Wing Thickness on Rolling Effectiveness and Drag of Unswept Wings at Mach Numbers Between 0.4 and 1.7

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Fields, E M↗

NASA NTRS1952

Summary of Some Effective Aerodynamic Twisting-moment Coefficients of Various Wing-control Configurations at Mach Numbers from 0.6 to 1.7 as Determined from Rocket-powered Models

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Strass, H Kurt↗

NASA NTRS1956

Free-flight Investigation at Mach Numbers Between 0.5 and 1.7 of the Zero-lift Rolling Effectiveness and Drag of Various Surface, Spoiler, and Jet Controls on an 80 Degree Delta-wing Missile

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Schult, Eugene D↗

NASA NTRS1957

Dynamic stability investigation of two right circular cylinders in axial free-flight at Mach numbers from 0.4 to 1.7 : fineness-ratio-2.56 cylinder and fineness-ratio-4.0 cylinder with flared afterbody

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Mcfall, John C , Jr↗

NASA NTRS1957

Effects of Wing Warp on the Lift, Drag, and Static Longitudinal Stability Characteristics of an Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1.86 at Mach Numbers from 1.1 to 1.7

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Gillespie, Warren, Jr↗

NASA NTRS1957

Lateral Stability Investigation at Mach Numbers from 0.8 to 1.7 of Two Rocket-boosted Models of an Airplane Configuration with a 45 Degree Swept Wing and a Low Horizontal Tail

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Mcfall, John C , Jr↗

NASA NTRSDate not supplied

Supersonic External-Compression Inlets for Mach 1.4 to 2.0

A series of supersonic, external-compression inlets were designed for freestream Mach numbers of Mach 1.4, 1.7, and 2.0. The types of inlets included axisymmetric pitot, axisymmetric spike, two-dimensional, two-dimensional bifurcated, and streamline-traced inlets. The inlets were designed as isolated from an aircraft with freestream conditions, engine-face geometry, and flow rates established from a reference NASA commercial aircraft concept. The inlets were designed using the NASA Supersonic Inlet Design and Analysis (SUPIN) Tool and the inlet performance was obtained from computational fluid dynamics (CFD) simulations. The study compares the physical dimensions and aerodynamic performance of the inlets to provide reference information for the selection of inlet types for commercial supersonic aircraft.

Supersonics↗

NASA NTRSDate not supplied

Supersonic External-Compression Inlets for Mach 1.4 to 2.0

Supersonics↗

NASA NTRS1954

An experimental investigation of four triangular-wing-body combinations in sideslip at Mach numbers 0.6, 0.9, 1.4, and 1.7

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Christensen, Frederik B↗

NASA NTRS1956

Longitudinal Stability Investigation for a Mach Number Range of 0.8 to 1.7 of an Airplane Configuration with a 45 Degree Swept Wing and a Low Horizontal Tail

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Mcfall, John C , Jr↗