National Advisory Committee for Aeronautics (NACA) - 198 Matching Results

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The additional-mass effect of plates as determined by experiments

Description: From Introduction: "The apparent increase in the inertia properties of a body moving in a fluid medium has been called the additional-mass effect. This report presents a resume of test procedures and results of experimental determinations of the additional-mass effect of flat plates. In addition to data obtained from various foreign sources and from a NACA investigation in 1933, the results of tests recently conducted by the National Advisory Committee for Aeronautics are included."
Date: 1941
Creator: Gracey, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps

Description: "Additional tests as recommended in reference 1 were made in the 7- by 10-foot wind tunnel of the 1/8-scale model of the Brewster F2A airplane to determine the angle of attack of horizontal tail and the elevator angles required for trim with flaps down" (p. 1).
Date: October 1941
Creator: Lowry, John G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Slot-Lip Aileron and Slotted Flap for Dive Brakes

Description: From Introduction: "As a part of this investigation, a study is being made of test results obtained during the development of devices designed primarily for other purposes, such as high lift or lateral control, but which may also be used for dive control. These results have been reanalyzed and are herein presented in a form that should make them convenient for design purposes."
Date: April 1941
Creator: Rogallo, F. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Factors Affecting the Ability of a Pilot to Return an Airplane to Level From a Banked Attitude by Use of the Rudder Alone and Without Change of Heading

Description: Report presenting a study of the aerodynamic factors upon which the ability to perform the maneuver depends in an attempt to obtain a better understanding of the conditions involved and, if possible, to evolve criterions that may be used during design.
Date: October 1941
Creator: Harmon, S. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The aerodynamics of a wind-tunnel fan

Description: From Introduction: "This paper deals only with the aerodynamics of the fan proper and demonstrates the manner in which the radial distribution of axial velocity of fluid through a fan is governed by geometry of the fan itself."
Date: August 1941
Creator: Corson, Blake W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Air Transport by Gliders: Some Technical Observations

Description: This short analysis may be useful in determining the real tactical possibilities of "glider trains" and in adopting the course to be followed in possible studies of these questions. In this analysis most prominent are: (a) the power required for the train in level flight; (b) its speed; (c) climb; and (d) the type of airplane best suited for towing as well as design requirements for transport gliders.
Date: June 1941
Creator: Stepniewski, Wieslaw
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aluminum-Zinc-Magnesium-Copper Casting Alloys

Description: From Introduction: "This paper contains data on the mechanical properties of sand-cast test bars having a considerable range in zinc, magnesium, and copper content and more detailed data on the properties and foundry characteristics of an aluminum-zinc-magnesium-copper alloy having a preferred composition for high strength and ductility."
Date: July 1941
Creator: Kempf, L. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Ground Effect on the Lifting Airscrew

Description: "A study is presented of ground effect as applied to the lifting airscrew of the type used in modern gyroplanes and helicopters. The mathematical analysis of the problem has been verified by tests made of three rotor models in the presence of a large circular "ground plane." The results of the study are presented in the form of convenient charts" (p. 1).
Date: December 1941
Creator: Knight, Montgomery & Hefner, Ralph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Determination of Control System Pulley-Axis Angles

Description: From Introduction: "The ideas developed in this paper are presented as a means of saving the designer's time and as a method of reduction of control-system friction by an accurate calculation of pulley-axis angles without the errors and difficult checking incident to any graphical method."
Date: September 1941
Creator: Driggs, I. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analytical study of wing and tail loads associated with an elevator deflection

Description: From Introduction: "The present paper covers step 1 of the outlined investigation, includes methods of computing the variation of wing and tail loads, and gives numerical results of the application of the theory to the BT-9B airplane. Finally, theoretical formulas are developed and charts are given for computing the maximum increments of wing load, the down-tail load, and the up-tail load following a given elevator displacement."
Date: June 1941
Creator: Pearson, H. A. & Garvin, J. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending of Rectangular Plates With Large Deflections

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… more
Date: May 27, 1941
Creator: Levy, Samuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary Layer Removal by Suction

Description: Flight-test data and wind-tunnel data on suction profiles are substantially in agreement. The lift values found in the model test can be actually flown and used as a basis for the design. To visualize the action of the suction, the flow conditions with and without suction on the upper surface were photographed; figures 12 to 15 are sections of the film.
Date: April 1941
Creator: Schrenk, O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Buckling Tests on Eccentrically Loaded Beam Columns

Description: "Formulas are obtained for computing the buckling load of rods eccentrically loaded at each end, the computation being extended in particular to the inelastic range. The test results are graphically presented on three sets of curves. Two of these, at least for the elastic range, are independent of the material tested. The third set, which is independent of the material, possesses greater clearness and is therefore used for comparing the test results with the theoretical" (p. 1).
Date: October 1941
Creator: Cassens, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Calculation of Span Load Distributions of Swept-Back Wings

Description: "Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9" (p. 1).
Date: December 1941
Creator: Mutterperl, William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of Naca 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps

Description: "At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord split flaps, deflected 60 degrees, in the center of the wing and having flat span to wing span ratios of 0.3, 0.5, 0.7, and 1.0, respectively" (p. 1).
Date: January 1941
Creator: Greenberg, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of NACA 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps

Description: "At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord spit flaps, deflected 60 deg span ratios of 0.3, 0.5, 0.7 and 1.0 respectively. In order to get data from which to calculate the characteristics of the flapped wing, the investigation was extended to include tests of the four rectangular airfoils of the NACA 4… more
Date: January 1941
Creator: Greenberg, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Combined Beam-Column Stresses of Aluminum-Alloy Channel Sections

Description: "The results of tests of 65 specimens of aluminum-alloy channel sections are graphed for stresses due to axial and bending loads as functions of the ratio of length of specimen to its radius of gyration, and from these data a suggested design chart is derived that is suitable for ready use" (p. 1).
Date: September 1941
Creator: Hutton, J. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Automatic Control Systems

Description: This report deals with a reciprocal comparison of an automatic pressure control, an automatic rpm control, an automatic temperature control, and an automatic directional control. It shows the difference between the "faultproof" regulator and the actual regulator which is subject to faults, and develops this difference as far as possible in a parallel manner with regard to the control systems under consideration. Such as analysis affords, particularly in its extension to the faults of the actual… more
Date: February 1941
Creator: Oppelt, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Intercooler Characteristics

Description: "A method is presented of comparing the performance, weight, and general dimensional characteristics of inter-coolers. The performance and dimensional characteristics covered in the comparisons are cooling effectiveness, pressure drops and weight flows of the charge and cooling air, power losses, volume, frontal area, and width. A method of presenting intercooler data is described in which two types of charts are plotted; (1) A performance chart setting forth all the important characteristics o… more
Date: May 1941
Creator: Reuter, J. George & Valerino, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of stress-strain curves obtained by single-thickness and pack methods

Description: Report presenting an apparatus for supporting a single thickness of sheet against buckling so that its compressive yield strength can be determined by the single-thickness method. The results of testing are compared with those from two other methods. This method results in substantial cost savings as compared to the pack method.
Date: August 1941
Creator: Paul, D. A.; Howell, F. M. & Grieshaber, H. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel

Description: "The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces" (p. 1).
Date: July 1941
Creator: Greenberg, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compressibility Effects in Aeronautical Engineering

Description: "Compressible-flow research, while a relatively new field in aeronautics, is very old, dating back almost to the development of the first firearm. Over the last hundred years, researches have been conducted in the ballistics field, but these results have been of practically no use in aeronautical engineering because the phenomena that have been studied have been the more or less steady supersonic condition of flow. Some work that has been done in connection with steam turbines, particularly noz… more
Date: August 1941
Creator: Stack, John
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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