Technical Report Archive and Image Library (TRAIL) - 5,163 Matching Results

Search Results

An experimental investigation of the flow phenomena over bodies at high angles of attack at a Mach number of 2.01

Description: Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.
Date: October 27, 1955
Creator: Gapcynski, John P.
Partner: UNT Libraries Government Documents Department

Modified tubular combustor as high-temperature gas generators

Description: A pair of combustors and transition liners in a quarter-annular, direct-connect assembly was operated at temperatures up to 2400 degrees F to determine the feasibility of using production-type combustor systems as high-tmeperature gas generators for turbine-cooling studies. Operation at high temperatures for 32 hours was possible when minor liner modifications were made that provided greater cooling-air flow between the turbine casing and interior components.
Date: October 21, 1955
Creator: Friedman, Robert & Zettle, Eugene V
Partner: UNT Libraries Government Documents Department

Performance and component frontal areas of a hypothetical two-spool turbojet engine for three modes of operation

Description: Engine performance is better for constant outer-spool mechanical-speed operation than for constant inner-spool mechanical-speed operation over most of the flight range considered. Combustor and afterburner frontal areas are about the same for the two modes. Engine performance for a mode characterized by a constant outer-spool equivalent speed over part of the flight range and a constant outer-spool mechanical speed over the rest of the flight range is better that that for constant outer-spool mechanical speed operation. The former mode requires larger outer-spool centrifugal stresses and larger component frontal areas.
Date: December 19, 1955
Creator: Dugan, James F , Jr
Partner: UNT Libraries Government Documents Department

Transonic wind-tunnel investigation of effects of windshield shape and canopy location on the aerodynamic characteristics of canopy-body combinations

Description: From Summary: "Aerodynamic data have been obtained for a fuselage forebody alone and for canopy-body configurations consisting of four different canopies mounted on a fuselage forebody. Two of the canopies had the same shape and size rearward of the windshield but one had a "flat" and the other a "vee" windshield. The remaining two canopies were located at different body stations and were geometrically similar. The data indicated that the drag of the flat-windshield model was consistently lower than that of the vee-windshield model."
Date: September 20, 1955
Creator: Cornette, Elden S. & Robinson, Harold L.
Partner: UNT Libraries Government Documents Department

Transonic wind-tunnel investigation of the aerodynamic loading characteristics of a 60 degree delta wing in the presence of a body with and without indentation

Description: Report presenting an investigation in the transonic pressure tunnel to determine the aerodynamic loading characteristics of a 60 degree delta wing in the presence of a body with and without body indentation in accordance with the transonic-area-rule concept. Tests covered a range of angles of attack and Mach numbers. Results regarding force and moment coefficients and curves are provided.
Date: September 15, 1955
Creator: Mugler, John P., Jr.
Partner: UNT Libraries Government Documents Department

Preliminary Free-Jet Performance of XRJ43-MA-3 Flight-Weight Ram-Jet Engine at Mach Numbers of 2.35, 2.50, and 2.70

Description: The performance of the XRJ43-MA-3 flight-weight ram-jet engine has been investigated in a free-jet facility as part of the development program for the "Bomarc," ram-jet powered, interceptor-type missile. The engine performance was obtained at Mach number s of 2.35, 2.50, and 2.70, altitudes from 50,000 to 75,000 feet, and Miami hot day and cold day inlet temperatures at an angle of attack of +4 deg. At each flight condition investigated, the engine control set an inner-ring fuel flow which was held constant as outer-ring fuel flow was varied. Combustion screech, which occurred more readily at the higher combustor pressures, fuel-air ratios, and inlet temperatures, resulted in discontinuities in the performance curves and an improvement in engine performance. The maximum time that the engine was allowed to operate continuously in the screech region was approximately 4 minutes. For these periods of time at the pressure levels investigated, no serious damage was evident. At a given fuel-air ratio, increasing the altitude or inlet temperature in the range investigated resulted in small reductions in net thrust coefficient. An increase in the flight Mach number raised the combustion efficiency but had little effect on the net thrust coefficient. Because conditions external to the engine did not simulate the actual flight conditions, no valid check of the durability of the combustion chamber and exhaust nozzle was obtained. All other engine components operated satisfactorily at least for at total burning time of 5 hours and high fuel-air-ratio operation of 35 minutes.
Date: November 18, 1955
Creator: McAulay, John E. & Prince, William R.
Partner: UNT Libraries Government Documents Department

Comparative dispersion data from ground-launched 2.25-inch rockets equipped with cruciform and monoplane fins

Description: Report presenting testing of about 150 rounds of 2.25-inch subcaliber aircraft rockets equipped with standard cruiform fins and twisted monoplane fins. No significant difference in dispersion was observed for the different configurations of fins on the rockets. Results regarding the stability of the different types of rockets, and general characteristics of the flight paths are provided.
Date: November 1, 1955
Creator: Purser, Paul E.
Partner: UNT Libraries Government Documents Department

Performance characteristics of cylindrical target-type thrust reversers

Description: From tests on cylindrical target-type thrust reversers, it was found that the reverser frontal area, lip angle, end-plate angle, and end-plate depth had important effects on reverse-thrust performance. Frontal area, reverser depth, lip angle, and end-plate angele had important effects on the spacing required for unrestricted nozzle flow. For reverse-thrust ratios greater than 64 percent, the reversed flow attached to the 7 degree cowl in quiescent air. Swept-type cylindrical reversers were generally unstable. The thrust-modulation characteristics of a cylindrical target-type thrust reverser were found to be satisfactory.
Date: January 11, 1956
Creator: Steffen, Fred W & Mcardle, Jack G
Partner: UNT Libraries Government Documents Department

Comparison of performance and component frontal areas of hypothetical two-spool and one-spool turbojet engines

Description: For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.
Date: January 17, 1956
Creator: Dugan, James F , Jr
Partner: UNT Libraries Government Documents Department