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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 145 records · Page 8

All sources NASA NTRS DOE OSTI

NASA NTRS1952

Low-speed Longitudinal Aerodynamic Characteristics of a Twisted and Cambered Wing of 45 Degree Sweepback and Aspect Ratio 8 with and Without High-lift and Stall-control Devices and a Fuselage at Reynolds Numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6

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Salmi, Reino J↗

NASA NTRS1952

Investigation of the effects of variations in the Reynolds number between 0.4 x 10(exp 6) 3.0 x 10(exp 6) on the low-speed aerodynamic characteristics of three low-aspect-ratio symmetrical wings with rectangular plan forms

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Jones, George W , Jr↗

NASA NTRS1952

Effects of twist and camber on the low-speed longitudinal stability characteristics of a 45 degree sweptback wing of aspect ratio 8 at Reynolds numbers from 1.5 x 10(exp 6) to 4.8 x 10(exp 6) as determined by pressure distributions, force tests

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Pratt, George L↗

NASA NTRS1953

Wind-tunnel Investigation of Stall Control by Suction Through a Porous Leading Edge on a 37 Degree Sweptback Wing of Aspect Ratio 6 at Reynolds Numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6)

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Graham, Robert R↗

NASA NTRS1953

Low-speed longitudinal characteristics of an unswept hexagonal wing with and without a fuselage and a horizontal tail located at various positions at Reynolds numbers from 2.8 x 10(exp 6) to 7.6 x 10(exp 6)

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Foster, Gerald V↗

NASA NTRS1953

Aerodynamics of Slender Bodies at Mach Number of 3.12 and Reynolds Numbers from 2 x 10(exp 6) to 15 x 10(exp 6) III : Boundary Layer and Force Measurements on a Slender Cone-cylinder Body of Revolution

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Jack, John R↗

NASA NTRS1953

Experimental Investigation of the Effects of Support Interference on the Pressure Distribution of a Body of Revolution at a Mach Number of 3.12 and Reynolds Numbers from 2 x 10(exp 6) to 14 x 10(exp 6)

A compilation of available information on the problem of support interference at transonic and supersonic speeds is presented. (author)

Baughman, L Eugene↗

NASA NTRS1953

Experimental Investigation of the Zero-lift Drag of a Fin-stabilized Body of Fineness Ratio 10 at Mach Numbers Between 0.6 and 10

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James, Carlton S↗

NASA NTRS1954

Subsonic investigation of effects of body indentation on zero-lift drag characteristics of a 45 degree sweptback wing-body combination with natural and fixed boundary-layer transition through a range of Reynolds number from 1 x 10(exp 6) to 8 x 10(ex

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Braslow, Albert L↗

NASA NTRS1955

Effects of Increasing Reynolds Number from 2 x 10(exp 6) to 6 x 10(exp 6) on the Aerodynamic Characteristics at Transonic Speeds of a 45 Degree Swept Wing with 6 Degree Leading-edge Droop

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Schmeer, James W↗

NASA NTRS1955

Analysis of aerodynamic blade-loading-limit parameters for NACA 65-(C(sub zeta(sub o)) A(sub 10)) 10 compressor-blade sections at low speeds

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Savage, Melvyn↗

NASA NTRS1957

Two-dimensional Cascade Tests of NACA 65-(c(sub Zeta)(sub O))a(sub 10))10 Blade Sections at Typical Compressor Hub Conditions for Speeds up to Choking

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Emery, James C↗

NASA NTRS1950

Positioning Investigation of Single Slotted Flaps on a 47.7 Degrees Sweptback Wing at Reynolds Numbers of 4.0 x 10(exp 6) and 6.0 x 10(exp 6)

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Spooner, Stanley H↗

NASA NTRS1954

Comparison of Low-speed Rotor and Cascade Performance for Medium-camber NACA 65-(c(sub Lo)a(sub 10) 10 Compressor-blade Sections over a Wide Range of Rotor Blade-setting Angles at Solidities of 1.0 and 0.5

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Ashby, George C , Jr↗

NASA NTRS1954

Pressure Recovery and Mass-flow Performance of Four Annular Nose Inlets Operating in Mach Number Region of 3.1 and Reynolds Number Range of Approximately 0.45 x 10(exp 6) to 2.20 x 10(exp 6)

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Hunczak, Henry R↗

NASA NTRS2003

Flexwall Hydraulic Hose Replacement in the NASA Glenn 10- by 10-Foot Supersonic Propulsion Wind Tunnel

The space-time conservation-element and solution-element method is employed to numerically study the near-field screech-tone noise of a typical underexpanded circular jet issuing from a sonic nozzle. Both axisymmetric and fully three-dimensional computations are carried out. The self-sustained feedback loop is properly simulated. The computed shock-cell structure, acoustic wave length, screech-tone frequency, and sound-pressure levels are in good agreement with existing experimental results.

Smith, Larry E.↗

NASA NTRS2002

Sonic Boom Testing Performed in NASA Glenn Research Center's 10- by 10-Foot Supersonic Wind Tunnel

One of the current impediments to the establishment of supersonic transports as a viable part of the commercial aviation fleet is the sonic boom effect. This effect is created when a vehicle achieves supersonic speeds and creates a shock wave (an immediate pressure change) that impinges on the ground. The resulting sonic boom can be both heard and felt on the ground, and it traverses the ground along the flight path of the vehicle. The environmental impact of this sonic boom effect is currently regulated by only allowing supersonic flight on over-water flight paths. The ability to measure the pressure signature of an aircraft configuration would allow researchers to identify the sources and the relative magnitude of that source on the aircraft pressure signature. It would also allow for the development and validation of computer codes to predict the sonic boom effects of an aircraft configuration.

Stark, David E.↗

NASA NTRS2014

Toxicological Assessment of ISS Air and Water Quality: November 10, 2013 - March 10, 2014 (Increment 38) and Orb-1 First Ingress

Based on these limited data, air quality was nomial on ISS for this period, and potable water remains acceptable for crew consumption.

Meyers, Valerie↗