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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

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

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