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The A. B. Flygindustri "K 37" (Swedish Junkers): A Low-Wing All-Metal Military Airplane

Description: Report discusses the characteristics of the K 37 all-metal long-wing monoplane and its use for long-distance scouting, as a day bomber, and as a heavy fighting airplane. Its engines, climbing capacity, action radius, bombing installation, fuselage, controls, and landing gear are explored in depth.
Date: October 1929
Creator: United States. National Advisory Committee for Aeronautics.
Item Type: Refine your search to only Report
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N.A.C.A. Recording Air Speed Meter

Description: A new type of air speed meter is described which was designed by the technical staff of the National Advisory Committee for Aeronautics. The instrument consists essentially of a tight metal diaphragm of high natural period which is acted upon by the pressure difference of a pitot-static head. The resulting deflection of this diaphragm is recorded optically on a moving film.
Date: October 1921
Creator: Norton, F. H.
Item Type: Refine your search to only Report
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N.A.C.A. Stall-Warning Indicator

Description: "The stall-warning indicator employs a total-head tube located close to the wing surface in a region wherein local stalling occurs before the main portion of the wing stalls. The artificial production of a localized stalled region is accomplished by means of a sharp leading edge extending a few inches along the span. An abrupt drop in the total pressure relative to a static reference taken at some convenient point occurs at the stall in this region" (p. 1).
Date: October 1938
Creator: Thompson, F. L.
Item Type: Refine your search to only Report
open access

An Accurate Method of Measuring the Moments of Inertia of Airplanes

Description: From Summary: "This note contains a description of an improved apparatus and procedure used by the NACA for determining the moments of inertia of airplanes. The method used, based on the pendulum theory, is similar to that previously used, but a recent investigation of its accuracy has resulted in the improvements described herein. The error, when using the new apparatus and procedure, has been found to be of the order of 1 per cent."
Date: October 1930
Creator: Miller, M. P.
Item Type: Refine your search to only Report
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Activation of hydrocarbons and the octane number

Description: This report presents an examination of the history of research on engine knocking and the various types of fuels used in the investigations of this phenomenon. According to this report, the spontaneous ignition of hydrocarbons doped with oxygen follows the logarithmic law within a certain temperature range, but not above 920 degrees K. Having extended the scope of investigations to prove hydrocarbons, the curves of the mixtures burned by air should then be established by progressive replacement… more
Date: October 1939
Creator: Peschard, Marcel
Item Type: Refine your search to only Report
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Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Description: From Introduction: "The configuration described in this paper represents one approach to such an airplane and the results of the wind-tunnel and tank evaluations are presented. In the present investigation, the aerodynamic longitudinal characteristics over a Mach number range from 0.6 to 1.97 were obtained."
Date: October 23, 1957
Creator: Petynia, William W.; Hasson, Dennis F. & Spooner, Stanley H.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics and Flap Loads of the Brake-Flap Installation on the 0.40-Scale Model of the F4F-3 Left Wing Panel

Description: "The data are presented in coefficient form and include lift, drag, and pitching-moment coefficients of the airfoil-flap comoinations and the normal-force, chord-force, and hinge-moment coefficients of the upper (perforated split) flap and lower (slotted) flap" (p. 1).
Date: October 1942
Creator: Purser, Paul E. & Liddell, Robert B.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees

Description: Report discussing testing to determine the supersonic aerodynamic characteristics of four sweptback wings and wing-body configurations at several angles. Information about basic wing data, modifications to the 60 degree wing, the effects of sweep, and effects of fuselage are included.
Date: October 10, 1950
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at high speeds of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Description: From Introduction: "The aerodynamic characteristics of a series of 10-foot-diameter propellers are being investigated in the Langley 16-foot high-speed tunnel in a comprehensive propeller research program. Using high-critical-speed NACA 16-series airfoil sections (reference 1), these propellers are designed to have Betz minimum induced-energy loss loading (reference 2) for a blade angle of 45^o at the 0.7 radius, when used as a four-blade propeller operating at an advance ratio of approximately… more
Date: October 1, 1948
Creator: Solomon, William
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics at high speeds of full-scale propellers having Clark Y blade sections

Description: From Introduction: "The single purpose of this paper is to make available the data obtained from tests of these two Clark Y section propellers as quickly as possible with no attempt being made to analyze the results or to compare them with other high-speed-propeller test results."
Date: October 26, 1948
Creator: Johnson, Peter J.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics for Internal-Balance and Frise Type Ailerons on an NACA 6 Series Low-Drag Tip Section of the Wing for the XP-63 Airplane

Description: Report presenting testing in the two-dimensional turbulence tunnel of a model of the tip section of the wing of the XP-63 airplane. Several alterations of the skirts and balance on the internal-balance aileron were tested to obtain various aerodynamic characteristics of the aileron.
Date: October 1942
Creator: Underwood, William J.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Description: From Introduction: "This paper presents the results of tests made at a Mach number of 2.01 to determine the effect of body length on the longitudinal characteristics (zero roll angle) for five complete configurations as well as for the bodies alone, the bodies plus wings, and the bodies plus canard surfaces. The experimental results are compared with some simple theoretical estimates."
Date: October 30, 1953
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)

Description: Report presenting an investigation of the two-dimensional aerodynamic characteristics of 15 NACA airfoils at four Reynolds numbers. The results indicate that the drag coefficient at the design lift coefficient and the maximum lift coefficient are the most important aerodynamic characteristics and are most affected by Reynolds number changes.
Date: October 1949
Creator: Loftin, Laurence K., Jr. & Smith, Hamilton A.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of a 1/8-Scale Powered Model of a High-Speed Bomber With a Dual Pusher Propeller Aft of the Empennage

Description: Report presenting wind-tunnel tests made to determine the aerodynamic characteristics of a scale model of a high-speed bomber with a dual pusher propeller aft of the empennage. Some of the results discussed include longitudinal, lateral, and directional stability and control, the empennage design, and ground effects on the aerodynamic characteristics. The results indicate that this particular airplane has several advantages with regard to stability and control over the conventional-type single-… more
Date: October 12, 1945
Creator: Weiberg, James A. & Schnurbusch, Alfred W.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."
Date: October 21, 1949
Creator: Goodson, Kenneth W. & Morrison, William D., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Two All-Movable Wings Tested in the Presence of a Fuselage at a Mach Number of 1.9

Description: Report presenting testing of half-span models of two wings of different plan form as both all-movable and fixed surfaces in the presence of a half fuselage. All-movable surfaces are being considered for supersonic aircraft as possible angle-of-attack indicators, control surfaces, and all-movable wings. Results regarding the lift characteristics, center of pressure, and drag of the wings are provided.
Date: October 28, 1948
Creator: Conner, D. William
Item Type: Refine your search to only Report
open access

Aerodynamic coefficients for an oscillating airfoil with hinged flap, with tables for a Mach number of 0.7

Description: From Introduction: "The fundamental integral equation for the pressure distribution on an oscillating thin airfoil moving at subsonic speed has been derived by Possio in reference 1. Collocation procedures have been used by Possio, Frazer, and Skan, and others to obtain lift and moment on an oscillating first plate. An important contribution has been made by Dietze (see reference 2 and 3), who has developed an iterative procedure for numerical solution of Possio's integral equation."
Date: October 1950
Creator: Turner, M. J. & Rabinowitz, S.
Item Type: Refine your search to only Report
open access

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
open access

Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing

Description: From Summary: "Two topics of interest to persons attempting to apply the heat method of preventing ice formation on aircraft are considered. Surfaces moving through air at high speed are shown, both theoretically and experimentally, to be subject to important aerodynamic heating effects that will materially reduce the heat required to prevent ice. Numerical calculations of the path of water drops in an air stream around a circular cylinder are given. From these calculations, information is obta… more
Date: October 1940
Creator: Kantrowitz, Arthur
Item Type: Refine your search to only Report
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