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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 1,117 records · Page 62
All sourcesNASA NTRSDOE OSTI
NASA NTRS1992

Structural and aerodynamic considerations for an oblique all-wing aircraft

A key design issue for the Oblique All-Wing aircraft is the packaging of the payload compartment, the fuel tanks, and the other internal components within the airfoil. The internal arrangement of such vehicles is strongly coupled to the exterior vehicle geometry. For example, the height requirements of a passenger cabin directly influence the aircraft thickness and span. As a result, the internal arrangement strongly affects aerodynamic performance and structural weight. Configuration criteria are defined and/or discussed, and a baseline aircraft is developed. Also, some of the major tradeoffs that affect structural weight and aerodynamic performance are presented.

Waters, M. H.↗
NASA NTRS1992

Oblique wing supersonic transport concepts

The economic and technical features of two SST concepts that offer the potential of reducing the impact of the environmental constraints on the aircraft design and performance are presented. The potential economic performance of these aircraft is referenced to equivalent passenger size subsonic designs employing consistent design guidelines and assumptions. Total operating cost and airline return on investment are utilized for the economic comparisons.

Galloway, Thomas↗
NASA NTRS1992

Effects of turbine cooling assumptions on performance and sizing of high-speed civil transport

The analytical study presented examines the effects of varying turbine cooling assumptions on the performance of a high speed civil transport propulsion system as well as the sizing sensitivity of this aircraft to these performance variations. The propulsion concept employed in this study was a two spool, variable cycle engine with a sea level thrust of 55,000 lbf. The aircraft used for this study was a 250 passenger vehicle with a cruise Mach number of 2.4 and 500 nautical mile range. The differences in turbine cooling assumptions were represented by varying amount of high pressure compressor bleed air used to cool the turbines. It was found that as this cooling amount increased, engine size and weight increased, but specific fuel consumption (SFC) decreased at takeoff and climb only. Because most time is spent at cruise, the SFC advantage of the higher bleed engines seen during subsonic flight was minimized and the lower bleed, lighter engines led to the lowest takeoff gross weight vehicles. Finally, the change in aircraft takeoff gross weight versus turbine cooling level is presented.

Senick, Paul F.↗
NASA NTRS1988

A preliminary component analysis of a Mach-7 hypersonic vehicle

As research continues in the development of an aircraft capable of travelling at hypersonic flight velocities, both the propulsion and thermal management systems stand out as areas requiring innovative technological breakthroughs. For propulsion, the difficulty involves efficiently compressing and combusting hydrogen in a supersonic stream, i.e., developing a viable scramjet with thermal management, the challenge lies in development of materials and active cooling systems capable of handling the enormous heat fluxes associated with hypersonic flight. This paper focuses on these problems and presents component designs for both an active cooling system and an all-external-compression scramjet. These systems are mated to a Mach-6 passenger cruise aircraft whose aerodynamic configuration was derived from an optimization of NASA windtunnel test results. The following outlines the development of the configuration and then focuses in on the design of the two component systems.

Source record↗
NASA NTRS1988

Preliminary design of two transpacific high-speed civil transport

Two high-speed civil transport (HSCT) design concepts are presented. Both transports are designed for a 5500-n.m. range with 300 passengers. The first design concept is a Mach 2.5, joined-wing, single-fuselage transport. The second design concept is a Mach-4.0, twin-fuselage, variable-sweep wing transport. The use of conventional hydrocarbon fuels is emphasized to reduce the amount of change required in current airport facilities. Advanced aluminums are used in the designs when possible to reduce material and production costs over more exotic materials. Methods to reduce airport noise, community noise, and fly-over noise are incorporated into the designs. In addition, requirements set forth by the Federal Aviation Regulations (FARs) have been addressed.

Source record↗
NASA NTRS1921

The Caproni Seaplane

The Caproni Company recently built a seaplane of unusual design. The main supporting surfaces consisted of three triplanes in tandem, the lower wings being attached to the hull, which was described as providing accommodation for a hundred passengers. On one of the first flights, the seaplane fell into a lake, nose down, and was destroyed. The authors wish to show that this failure could have been predicted. The failure could have been predicted by applying some fundamental principles of aeronautics, especially those relating to longitudinal stability, the lack of which caused the loss of the seaplane.

Munk, Max↗
NASA NTRS1922

Report on the general design of commercial aircraft

Given here are evaluations of six different European aircraft from the point of view of a passenger. The aircraft discussed are the DH 34, the Handley-Page W8B, the Farman Goliath, the Potez IX, the Spad 33 (Berline), and the Fokker F.III. The airplanes were evaluated with regard to seating comfort, ventilation, noise, seating arrangements, cabin doors, baggage accommodation, interior arrangement of cabins, pilot's position and communication with the pilot, pilot accommodations, view from the cabin, safety, and lavatory accommodations.

Warner, Edward P↗
NASA NTRS1922

Night flying

Dr. Warner examines the utility and economy of flying at night when flying passengers. Some of the points discussed include lighted landing fields, the possibility of using airships, and the cost of landing fields.

Warner, Edward P↗
NASA NTRS1922

Subsidies for air transport

This article discusses the need for government subsidies to encourage the development of passenger and freight transport by air.

Warner, Edward P↗
NASA NTRS1922

Comfort in flight

Some advances in passenger comfort are discussed, namely, ventilated cabins, heating, seating arrangements, and doors.

Warner, Edward P↗
NASA NTRS1922

European air travel in 1922

This article discusses the different passenger air transport services offered in Europe. The author deals mainly with the service offered between different cities, in terms of time and cost.

Warner, Edward P↗
NASA NTRS1956

Initial results of a flight investigation of the wing and tail loads on an airplane equipped with a vane-controlled gust-alleviation system

Results are given of an analysis of wing and horizontal-tail spar strains measured on a twin-engine light transport airplane which was modified for the installation of a control system to alleviate airplane motions in turbulent air and thus improve passenger comfort. From a sample of the measurements obtained in flight through clear-air turbulence, normal acceleration at the airplane center of gravity was reduced 43 percent, wing main-spar bending strains were reduced, and wing-spar shear strains were increased. Horizontal-tail shear and bending strains were increased. Measurements of aerodynamic loads obtained in a pull-up with the gust-alleviation system in operation are also presented.

LOADS AND STRESSES, STRUCTURAL - DYNAMIC↗
NASA NTRS1925

European commercial aeronautics

During the months of June to September, 1924, I personally visited the principal airports of Europe and traveled as a passenger some 6500 air miles on English, French, Romanian, Polish, German and Dutch air lines in order to investigate the development of commercial aviation abroad. The results of the investigation are embodied in a series of reports, of which a summary of the general findings is given below.

Van Zandt, J Parker↗