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11 Matching Results
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Effect of Inlet Temperature on Rotating Stall and Blade Vibrations in a Multistage Axial-Flow Compressor
Report presenting rotating-stall and blade-vibration data for the first three rotor blade rows of a 13-stage axial-flow compressor at several inlet temperatures. Stall patterns of 1 through 5 stall zones were detected at all inlet temperatures in the equivalent compressor speed ranges between 4600 and 6200 rpm.
Date:
August 5, 1955
Creator:
Medeiros, Arthur A.; Calvert, Howard F. & Fenn, David B.
System:
The UNT Digital Library
Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane
Memorandum presenting rudder pulse maneuvers obtained with the Convair XF-92A delta-wing research airplane at an altitude of about 30,000 feet over a Mach number range of 0.52 to 0.92. Tests were made with and without a wing fence. By analyzing the maneuvers, the characteristics of the airplane transient, airplane stability derivatives, and frequency-response characteristics were measured.
Date:
August 5, 1955
Creator:
Holleman, Euclid C.
System:
The UNT Digital Library
Stall and flame-out resulting from firing of armament
Report presenting an analysis of the causes of compressor stall and flame-out when armament is fired during flight at high altitudes. Experimental data are also presented. The increase in compressor-inlet temperature during armament firing was found to be the most important single factor affecting engine performance.
Date:
August 5, 1955
Creator:
Childs, J. Howard; Kochendorfer, Fred D.; Lubick, Robert J. & Friedman, Robert
System:
The UNT Digital Library
Aerodynamic characteristics of several tip controls on a 60 degree wing at a Mach number of 1.61
Report presenting an investigation at a Mach number of 1.61 to determine the control effectiveness characteristics of seven tip controls on a 60 degree delta wing. Pressure distribution measurements were made for a range of angles of attack and control deflections. Results regarding the effect of control deflection, effect of wing angle of attack, effect of hinge-line location, effect of fences, and effect of control size and location are provided.
Date:
August 5, 1954
Creator:
Lord, Douglas R. & Czarnecki, K. R.
System:
The UNT Digital Library
Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance
Report presenting ramjet engine performance data over a range of engine design variables to permit selection and evaluation of a ramjet engine configuration for a long-range supersonic missile. Results include engine thrust, drag, fuel consumption, area ratios, and weight, and are suitable for use in design studies of missiles incorporating either internally or externally mounted ramjet engines.
Date:
August 5, 1954
Creator:
Weber, Richard J. & Luidens, Roger W.
System:
The UNT Digital Library
Comparison Between Theoretical and Experimental Rates of Roll of Two Models with Flexible Rectangular Wings at Supersonic Speeds
"A comparison is presented between the experimentally measured and theoretically calculated (by the method of NACA TN 3067) rates of roll of two rocket-propelled models with flexible rectangular wings. The comparisons show that although there are large aeroelastic losses in rolling rate, the theory predicts the actual rate of roll accurately" (p. 1).
Date:
August 5, 1954
Creator:
Hedgepeth, John M. & Kell, Robert J.
System:
The UNT Digital Library
Investigation of the Effect of Balancing Tabs on the Hinge-Moment Characteristics of a Trailing-Edge Flap-Type Control on a Trapezoidal Wing at a Mach Number of 1.61
Report presenting an investigation at Mach number 1.61 to determine the effect of 10-percent control are attached tabs on the hinge-moment characteristics of a trailing-edge flap-type control on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. Results regarding hinge-moment coefficients, tab parameters, and control effectiveness are provided.
Date:
August 5, 1954
Creator:
Lord, Douglas R. & Driver, Cornelius
System:
The UNT Digital Library
A Compilation of Summaries From NACA Reports on Fuels Research, 1945-1952
Memorandum compiling summaries from NACA reports on fuel that were published between July 1945 and 1952. The summaries are intended to be detailed enough to eliminate the need to obtain the complete report.
Date:
August 5, 1953
Creator:
DiPiazza, J. T.
System:
The UNT Digital Library
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)
Report presenting an experimental investigation performed to determine the effect on base and forebody pressures of using a sting modified with varying length splitter plates and fins instead of a conventional sting to support a cone-cylinder body of revolution.
Date:
August 5, 1953
Creator:
Baughman, L. Eugene & Jack, John R.
System:
The UNT Digital Library
Magnesium-slurry combustion performance in 6.5-inch-diameter ram-jet engine mounted in connected-pipe facility
Report presenting an investigation of the performance of slurry fuels consisting of 50 percent magnesium powder in a hydrocarbon carrier in a flight-type, 6.5-inch-diameter ramjet engine mounted in a connected-pipe facility. Results regarding the slurry performance and a comparison of slurry and ethylene performance are provided.
Date:
August 5, 1953
Creator:
Branstetter, J. Robert; Gibbs, James B. & Kaufman, Warner B.
System:
The UNT Digital Library
Effects of simulated skin wrinkles on the wing surface on the aerodynamic characteristics of two wing-body combinations employing wings of low aspect ratio at subsonic and supersonic speeds
Report presenting the results of an investigation to determine the effects of simulated skin wrinkling of the wing surface on the aerodynamic characteristics of two wing-body combinations. The lift, drag, and pitching moment of a low-wing wing-body combination with a plane triangular wing of aspect ratio 3 are presented for a range of Mach and Reynolds numbers.
Date:
August 5, 1952
Creator:
Heitmeyer, John C. & Smith, Willard G.
System:
The UNT Digital Library