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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Reports
 Collection: National Advisory Committee for Aeronautics Collection
Critical Compressive Stress for Flat Rectangular Plates Supported Along All Edges and Elastically Restrained Against Rotation along the Unloaded Edges

Critical Compressive Stress for Flat Rectangular Plates Supported Along All Edges and Elastically Restrained Against Rotation along the Unloaded Edges

Date: January 1, 1942
Creator: Lundquist, Eugene E & Stowell, Elbridge Z
Description: A chart is presented for the values of the coefficient in the formula for the critical compressive stress at which buckling may be expected to occur in flat rectangular plates supported along all edges and, in addition, elastically restrained against rotation along the unloaded edges. The mathematical derivations of the formulas required in the construction of the chart are given.
Contributing Partner: UNT Libraries Government Documents Department
Internal-flow systems for aircraft

Internal-flow systems for aircraft

Date: January 1, 1941
Creator: Rogallo, F M
Description: An investigation has been made to determine efficient arrangements for an internal-flow system of an aircraft when such a system operates by itself or in combination with other flow systems. The investigation included a theoretical treatment of the problem and tests in the NACA 5-foot vertical wind tunnel of inlet and outlet openings in a flat plate and in a wing.
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Determination of control-surface characteristics from NACA plain-flap and tab data

Determination of control-surface characteristics from NACA plain-flap and tab data

Date: January 1, 1941
Creator: Ames, Milton B & Sears, Richard I
Description: The data from previous NACA pressure-distribution investigations of plain flaps and tabs with sealed gaps have been analyzed and are presented in this paper in a form readily applicable to the problems of control-surface design. The experimentally determined variation of aerodynamic parameters with flap chord and tab chord are given in chart form and comparisons are made with the theory. With the aid of these charts and the theoretical relationships for a thin airfoil, the aerodynamic characteristics for control surfaces of any plan form with plain flaps and tabs with sealed gaps may be determined. A discussion of the basic equations of the thin-airfoil theory and the development of a number of additional equations that will be helpful in tail design are presented in the appendixes. The procedure for applying the data is described and a sample problem of horizontal tail design is included. The data presented and the method of application set forth in this report should provide a reasonably accurate and satisfactory means of computing the aerodynamic characteristics of control surfaces.
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The calculated effect of various hydrodynamic and aerodynamic factors on the take-off of a large flying boat

The calculated effect of various hydrodynamic and aerodynamic factors on the take-off of a large flying boat

Date: January 1, 1940
Creator: Olson, R E & Allison, J M
Description: Report presents the results of an investigation made to determine the influence of various factors on the take-off performance of a hypothetical large flying boat by means of take-off calculations. The factors varied in the calculations were size of hull (load coefficient), wing setting, trim, deflection of flap, wing loading, aspect ratio, and parasite drag. The take-off times and distances were calculated to the stalling speeds and the performance above these speeds was separately studied to determine piloting technique for optimum take-off.
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Effect of aging on mechanical properties of aluminum-alloy rivets

Effect of aging on mechanical properties of aluminum-alloy rivets

Date: January 1, 1941
Creator: Roop, Frederick C
Description: Curves and tabular data present the results of strength tests made during and after 2 1/2 years of aging on rivets and rivet wire of 3/16-inch nominal diameter. The specimens were of aluminum alloy: 24s, 17s, and a17s of the duralumin type and 53s of the magnesium-silicide type.
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Normal-pressure tests of circular plates with clamped edges

Normal-pressure tests of circular plates with clamped edges

Date: January 1, 1942
Creator: Mcpherson, Albert E; Ramberg, Walter & Levy, Samuel
Description: A fixture is described for making normal-pressure tests of flat plates 5 inches in diameter in which particular care was taken to obtain rigid clamping at the edges. Results are given for 19 plates, ranging in thickness form 0.015 to 0.072 inch. The center deflections and the extreme-fiber stresses at low pressures were found to agree with theoretical values; the center deflections at high pressures were 4 to 12 percent greater than the theoretical values. Empirical curves are derived of the pressure for the beginning of the permanent set as a function of the dimensions of the plate and the tensile properties of the material.
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Normal-pressure tests of rectangular plates

Normal-pressure tests of rectangular plates

Date: January 1, 1942
Creator: Ramberg, Walter; Mcpherson, Albert E & Levy, Samuel
Description: Report presents the results of normal-pressure tests made of 56 rectangular plates with clamped edges and of 5 plates with freely supported edges. Pressure was applied and the center deflection and the permanent set at the center were measured. For some of the plates, in addition, strains and contours were measured.
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Bending of rectangular plates with large deflections

Bending of rectangular plates with large deflections

Date: January 1, 1942
Creator: Levy, Samuel
Description: The solution of Von Karman's fundamental equations for large deflections of plates is presented for the case of a simply supported rectangular plate under combined edge compression and lateral loading. Numerical solutions are given for square plates and for rectangular plates with a width-span ratio of 3:1. The effective widths under edge compression are compared with effective widths according to Von Karman, Bengston, Marguerre, and Cox and with experimental results by Ramberg, Mcpherson, and Levy. The deflections of a square plate under lateral pressure are compared with experimental and theoretical results by Kaiser. It is found that the effective widths agree closely with Marguerre's formula and with the experimentally observed values and that the deflections agree with the experimental results and with Kaiser's work.
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Ground effect on downwash angles and wake location

Ground effect on downwash angles and wake location

Date: January 1, 1942
Creator: Katzoff, S & Sweberg, Harold H
Description: A theoretical study was made of the reduction in downwash and the upward displacement of the wake in the presence of the ground, and some verification of theory was obtained by means of air-flow measurements made with a ground-board and image-wing combination. Methods are given for estimating the effects and numerous examples are included to illustrate the nature of these effects and to show their order of magnitude.
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High-Speed Tests of a Model Twin-Engine Low-Wing Transport Airplane

High-Speed Tests of a Model Twin-Engine Low-Wing Transport Airplane

Date: January 1, 1942
Creator: Becker, John V & LEONARD LLOYD H
Description: Report presents the results of force tests made of a 1/8-scale model of a twin-engine low-wing transport airplane in the NACA 8-foot high-speed tunnel to investigate compressibility and interference effects of speeds up to 450 miles per hour. In addition to tests of the standard arrangement of the model, tests were made with several modifications designed to reduce the drag and to increase the critical speed.
Contributing Partner: UNT Libraries Government Documents Department