Technical Report Archive and Image Library (TRAIL) - 86 Matching Results

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20,000 KW Nuclear Power Plant Study for United States Atomic Energy Commission

Description: Introduction: In September of 156, Gilbert Associates, Inc., entered into a contract with the United States of America, acting through the United States Atomic Energy Commission, for the study and preliminary design of a nuclear power plant being considered for integration into a central station power system at an overseas site.
Date: July 7, 1957
Creator: Gilbert Associates, Inc.
Partner: UNT Libraries Government Documents Department

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Description: Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory. A relatively simple, but general, theoretical method for calculating these load and moment characteristics is described, and the results from this method are found to be in good agreement with experiment provided the initial positions of the forebody vortices are known. It is shown that a simple application of slender-body theory can be used to predict the side loads due to sideslip that are contributed by a vertical tail on a wide variety of wing-body-tail combinations at low angles of attack. For several configurations, changes are indicated which reduced the vertical-tail loads per unit yawing moment of each complete configuration at large angles of attack. Some results are presented on the effect of high angle of attack on the induced-flow field and tail loads due to a wing at supersonic speed.
Date: July 23, 1957
Creator: Polhamus, E. C. & Spahr, J. R.
Partner: UNT Libraries Government Documents Department

Analysis of wing loads on a flexible swept-wing jet bomber during push-pull maneuvers

Description: Report presenting measurements of the loads of the wing of a Boeing B-47A medium bomber using strain-gage instrumentation during 23 symmetrical push-pull maneuvers at a variety of altitudes, Mach numbers, and gross weights. Time histories of aerodynamic shear, bending moment, and torque at each of four spanwise stations on the left wing and one on the right wing were created. Based on the results, presently available methods seem to be capable of predicting additional and basic loads accurately within the range of flight conditions in the test.
Date: July 23, 1957
Creator: Gainer, Patrick A. & Harper, Paul W.
Partner: UNT Libraries Government Documents Department

Comparative study of turbofan and turbojet engines

Description: Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.
Date: July 19, 1957
Creator: Kaufman, Harold R.; Benser, William A. & Gabriel, David S.
Partner: UNT Libraries Government Documents Department

The effects at subsonic speeds of wing fences and a tail on the longitudinal characteristics of a 63 degree swept-wing fuselage combination

Description: Report presenting wind-tunnel testing to evaluate the effects of wing fences and a tail on the longitudinal characteristics of a highly swept wing in combination with a fuselage. The model, which had a cambered and twisted wing with a leading-edge sweepback of 63 degrees and an aspect ratio of 3.5, was tested with fences of various shapes and swept and unswept horizontal tails. Results regarding exploratory tests, final-configuration tests, static longitudinal stability factors, and maximum lift-drag ratios are provided.
Date: July 2, 1957
Creator: Buell, Donald A. & Kolbe, Carl D.
Partner: UNT Libraries Government Documents Department

Effects of airplane flexibility on wing bending strains in rough air

Description: Some results on the effects of wing flexibility on wing bending strains as determined from flight tests of a Boeing B-29 and a Boeing B-47A airplane in rough air are presented. Results from an analytical study of the flexibility effects on the B-29 wing strains are compared with the experimental results. Both the experimental and calculated results are presented as frequency-response functions of the bending strains at various spanwise wing stations to gust disturbances. In addition, some indirect evidence of the effect of spanwise variations in turbulence on the response of the B-47A airplane is presented.
Date: July 1, 1957
Creator: Coleman, Thomas L.; Press, Harry & Shufflebarger, C. C.
Partner: UNT Libraries Government Documents Department

Estimation of incremental pitching moments due to trailing-edge flaps on swept and triangular wings

Description: Report presenting a method by which incremental pitching moments can be estimated for swept and triangular wings with arbitrary types of trailing-edge high-lift flaps. Span-loading theory is combined with two-dimensional airfoil data adjusted for the effects of sweep.
Date: July 1957
Creator: James, Harry A. & Hunton, Lynn W.
Partner: UNT Libraries Government Documents Department

Experimental investigation of effects of moderate sideslip on the flow fields near a 45 degree swept-wing-fuselage combination at low speed

Description: The flow fields near a 45 degree swept-wing-fuselage combination at moderate angles of sideslip (plus-or-minus 8 degrees), as determined experimentally at low speed, are presented as variations with chordwise distance for various spanwise and vertical locations and angles of attack. The results indicated that for positions close to the fuselage (on and near the plane of symmetry) changes in the angle of sideslip caused large changes in the flow-field characteristics and particularly in the local angles of sideslip, which in some cases were nearly double the static angle of sideslip. In general, the effects of changing the angle of sideslip on the flow-field characteristics for all of the outboard underwing locations were qualitatively similar, although conditions at the more inboard and outboard locations were somewhat more severe for lifting conditions than at the one-half semispan location. The chordwise gradients in the flow parameters for the underwing locations were more severe than for the fuselage locations although the effect of changing the angle of sideslip was less severe, in that the incremental changes in the local angles of sideslip were approximately equal to the static angle of sideslip. Flow conditions near the wing tip were found to be critically dependent on vertical location, with the largest sideslip-induced variations occurring at the nearest vertical locations. The results also indicated that for the outboard underwing locations the wing was the predominant factor in disturbing the field of flow for the conditions investigated.
Date: July 12, 1957
Creator: Alford, William J , Jr & King, Thomas J , Jr
Partner: UNT Libraries Government Documents Department

Experimental investigation of wing-aileron flutter characteristics of a 1/4-scale dynamic model of the X-1E airplane

Description: Report presenting testing of some of the flutter characteristics of a 1/4-scale model of the X-1E airplane wing and aileron in the transonic tunnel. The wing was tested as part of a complete model of an airplane over a Mach number range of 0.4 to 1.05 and a range of angles of attack. No stall flutter or classical flutter was encountered, but the results indicate that unstable aerodynamic damping is present on the ailerons at transonic speeds. Results regarding free play, angle of attack, aileron viscous dampers, and aileron tabs are provided.
Date: July 10, 1957
Creator: Gibson, Frederick W.; Igoe, William B. & Maloney, P. R.
Partner: UNT Libraries Government Documents Department

Exploratory tests of the behavior of several materials in a supersonic air jet at 4,000 degrees F

Description: From Summary: "Several materials have been tested in the ceramic-heated jet (laboratory model) at a Mach number of 1.96 with a stagnation temperature of approximately 4,000 degrees Fahrenheit. Test models made of molybdenum were less affected by temperature than titanium, stainless steel, and an alloy of 90 percent tungsten, 6 percent nickel, and 4 percent copper. Titanium and steel burn with highly exothermic reactions when subjected to the 4,000 degrees Fahrenheit air jet."
Date: July 29, 1957
Creator: Hopko, Russell N. & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department

Flight investigation of a supersonic propeller on a propeller research vehicle at Mach numbers to 1.01

Description: Report presenting a description of an NACA propeller research vehicle, the McDonnell XF-88B airplane, and the results of testing undertaken with it to determine the aerodynamic characteristics of a supersonic propeller at speeds up to a flight Mach number of 1.01. Results regarding thrust distributions, variation of aerodynamic characteristics with Mach number, installation effects, and a comparison of experimental results with theoretical calculations and other data are presented. The propeller efficiency was measured at 78 to 79 percent and thrust distributions were of a uniform nature.
Date: July 10, 1957
Creator: Hammack, Jerome B.; Kurbjun, Max C. & O'Bryan, Thomas C.
Partner: UNT Libraries Government Documents Department