A study of the overall problems of the true-temperature, hypersonic wind tunnel having semi-continuous operation and the preferred methods of solution.

"Supported by the McDonnell Aircraft Corporation under Contract no. 6140-20 P. O. 7S4899-R. Purdue Research Foundation. Research project no. 1717. Project Ae-33.

Mechanical properties of selected alloys at elevated temperatures

"PB 161761."

Magneto-fluid-mechanics of a viscous, electrically conducting fluid contained within two finite, concentric, rotating cylinders in the presence of a magnetic field,

"This research was supported by the McDonnell Aircraft Corporation under Contract no.6140-20 P.O.7S4899-R."

Merchant ship automation study; final report. Contract number MA-2228, U.S. Department of Commerce, Maritime Administration, Washington.

v.1.Summary and recommendations.--v.2.Automatic ship control and communications systems.--v.3.Appendices to 262 R 0012.--v.3.Appendices to 262 R 0012.--v.4.automatic control of engineering functions.--v.5.Appendices to 262 R 0014.--v.6.Powerplants and auxiliaries for automated ships.--v.7.Economic aspects of automation.--v.8.Legal implications of automation.

The slow motion of a permanently magnetized sphere in an electrically conducting medium,

"Research supported by the McDonnell Aircraft Corporation under Contract no. 6140-20 P.O. 7S4899-R and by the Purdue Research Foundation."

Liepmann's heat transfer method in aerothermochemistry.

"Purdue Research Foundation. Research Project no. 1717. Project Ae-33. This research was supported by the McDonnell Aircraft Corporation under Contract no. 6140-20 P.O. 7S4899-R."

An experimental study of the operating characteristics and electrode heat transfer of a direct current electric arc in a pressurized argon environment,

"Purdue Research Foundation. Research project no.1717. Project Ae-33. This research was supported by the McDonnell Aircraft Corporation under Contract no. 6140-20 P. O. 7S4899-R."

Instrumentation studies for plasma jet and hypersonic wind tunnel,

"This research was supported by the McDonnell Aircraft Corporation under Contract no. 6140-20 P.O. 7S4899-R."

Aircraft accident report : Saturn Airways, inc., Lockheed L-382, N14St, Springfield, Illinois, May 23, 1974 /

Mode of access: Internet.

Fundamental physics of the aircraft collision problem,

"Technical memo 465-1016-39."

Aircraft Marketing in an Era of Deregulation

The deregulation of commercial aviation has had far-reaching effects on all aspects of business. In the Spring 1984 issue, the author explored some of the changes in the domestic airline industry. This article discusses the effects of deregulation on another group - those who manufacture commercial aircraft.

Particle and gaseous emissions from commercial aircraft at each stage of the landing and takeoff cycle

A novel technique was used to measure emission factors for commonly used commercial aircraft including a range of Boeing and Airbus airframes under real world conditions. Engine exhaust emission factors for particles in terms of particle number and mass (PM2.5), along with those for CO2, and NOx were measured for over 280 individual aircraft during the various modes of landing/takeoff (LTO) cycle. Results from this study show that particle number, and NOx emission factors are dependant on aircraft engine thrust level. Minimum and maximum emissions factors for particle number, PM2.5, and NOx emissions were found to be in the range of 4.16×1015-5.42×1016 kg-1, 0.03-0.72 g.kg-1, and 3.25-37.94 g.kg-1 respectively for all measured airframes and LTO cycle modes. Number size distributions of emitted particles for the naturally diluted aircraft plumes in each mode of LTO cycle showed that particles were predominantly in the range of 4 to 100 nm in diameter in all cases. In general, size distributions exhibit similar modality during all phases of the LTO cycle. A very distinct nucleation mode was observed in all particle size distributions, except for taxiing and landing of A320 aircraft. Accumulation modes were also observed in all particle size distributions. Analysis of aircraft engine emissions during LTO cycle showed that aircraft thrust level is considerably higher during taxiing than idling suggesting that International Civil Aviation Organization (ICAO) standards need to be modified as the thrust levels for taxi and idle are considered to be the same (7% of total thrust) [1].