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 Collection: National Advisory Committee for Aeronautics Collection
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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.
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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 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 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 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.
Contributing Partner: UNT Libraries Government Documents Department
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 from 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 permanent set as a function of the dimensions of the plate and the tensile properties of the material.
Contributing Partner: UNT Libraries Government Documents Department
Square plate with clamped edges under normal pressure producing large deflections

Square plate with clamped edges under normal pressure producing large deflections

Date: January 1, 1942
Creator: Levy, Samuel
Description: A theoretical analysis is given for the stresses and deflections of a square plate with clamped edges under normal pressure producing large deflections. Values of the bending stress and membrane stress at the center of the plate and at the midpoint of the edge are given for center deflections up to 1.9 times the plate thickness. The shape of the deflected surface is given for low pressures and for the highest pressure considered. Convergence of the solution is considered and it is estimated that the possible error is less than 2 percent. The results are compared with the only previous approximate analysis known to the author and agree within 5 percent. They are also shown to compare favorably with the known exact solutions for the long rectangular plate and the circular plate.
Contributing Partner: UNT Libraries Government Documents Department
Ground effect on downwash angles and wake location

Ground effect on downwash angles and wake location

Date: May 1, 1942
Creator: Katzoff, S & Sweberg, Harold H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Engines and fuels

Engines and fuels

Date: August 1, 1923
Creator: unknown
Description: The report considers the effect on engines of the varying types of fuels now in use. Different types of fuels are examined and the influence of physical characteristics are considered.
Contributing Partner: UNT Libraries Government Documents Department
Aviation spirit - past, present, and future

Aviation spirit - past, present, and future

Date: September 1, 1923
Creator: Dunstan, A E & Thole, F B
Description: The volatile fuel of the high-speed internal combustion engine has, in the past, consisted almost exclusively of the lighter distillates from crude petroleum. Alternative and supplementary fuels are discussed such as: tetraline, dekalin, alcohol, cyclo-hexenes.
Contributing Partner: UNT Libraries Government Documents Department
Lautal as a material for airplane construction

Lautal as a material for airplane construction

Date: August 1, 1929
Creator: Brenner, Paul
Description: Lautal is a refinable aluminum alloy which, unlike duralumin, contains no magnesium. According to the statements of the Lauta Works, lautal contains: aluminum, 94%; copper, 4%; silicon, 2%. The use of lautal as a construction material is discussed in relation to specific weight, production methods, and riveting tests.
Contributing Partner: UNT Libraries Government Documents Department
Mechanical control of airplanes

Mechanical control of airplanes

Date: March 1, 1929
Creator: Boykow, H
Description: Before undertaking a detailed description of an automatic-control mechanism, I will state briefly the fundamental conditions for such devices. These are: 1) it must be sensitive at one or more reference values; 2) it must stop the angular motions of the airplane not produced by the pilot; and 3) it must be possible to switch it off and on by a simple hand lever.
Contributing Partner: UNT Libraries Government Documents Department