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Acceleration Measurements During Landings of a 1/5.5-Size Dynamic Model of the Columbia XJL-1 Amphibian in Smooth Water and in Waves: Langley Tank Model 208M, TED No. NACA 2336

Description: A 1/5.5-size powered dynamic model of the Columbia XJL-1 amphibian was landed in Langley tank no. 1 in smooth water and in oncoming waves of heights from 2.1 feet to 6.4 feet (full-size) and lengths from 50 feet to 264 feet (full-size). The motions and the vertical accelerations of the model were continuously recorded. The greatest vertical acceleration measured during the smooth-water landings was 3.1g.
Date: September 25, 1947
Creator: Clement, Eugene P. & Havens, Robert F.
Item Type: Refine your search to only Report
open access

Aerodynamic and Hydrodynamic Tests of a Family of Models of Flying-Boat Hulls Derived From a Streamline Body: NACA Model 84 Series

Description: Report presenting a series of related flying-boat hull forms with various combinations of aerodynamic and hydrodynamic requirements that were tested in an NACA tank and high-speed tunnel. Effects explored included varying the height of the bow, varying the height of the stern, increasing the angle of dead rise at the bow, decreasing the angle of dead rise on the afterbody, increasing the depth of step, increasing the angle of afterbody keel, adding chine flare, adding a third planing surface, a… more
Date: September 1943
Creator: Parkinson, John B.; Olson, Roland E.; Draley, Eugene C. & Luoma, Arvo A.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Description: "An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale model of the Fairchild Lark missile. The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses" (p. 1).
Date: September 28, 1949
Creator: Martin, Andrew & Hunter, Harlo A.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic-bump method

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuelage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date: September 6, 1949
Creator: King, Thomas J., Jr. & Myers, Boyd C., II
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of an Airfoil-Forebody Swept Flying-Boat Hull With a Wing and Tail Swept Back 51.3 Degrees at the Leading Edge

Description: Report discussing an investigation of the aerodynamic characteristics of an airfoil-forebody swept flying boat hull with a wing and tail swept back 51.3 degrees at the leading edge. The swept hull's minimum drag coefficient was about the same as the parent model or streamline model. Various combinations of flaps were also utilized.
Date: September 9, 1949
Creator: Naeseth, Rodger L. & MacLeod, Richard G.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels

Description: "Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections of the XF-12 airplane, were tested in the Langley two-dimensional low-turbulence tunnels to obtain their aerodynamic characteristics. Lift characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, 9,000,000, and 14,000,000, whereas drag characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, and 9,000,000. Pressure distributions were obtained for one of the ro… more
Date: September 27, 1945
Creator: Klein, Milton M.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils From Tests in the NACA Two-Dimensional Low-Turbulence Pressure Tunnel

Description: Report presenting two low-drag airfoils, the NACA 747A315 and the NACA 747A415, which are designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient and are tested in the tow-dimensional low-turbulence pressure tunnel.
Date: September 1944
Creator: von Doenhoff, Albert E. & Stivers, Louis S., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8

Description: Report presenting an investigation to determine the aerodynamic characteristics of a group of NACA 16-series airfoils related in camber and thickness over a range of Mach numbers. All of the currently available force-test data for NACA 16-series airfoils obtained under the same test conditions in the 24-inch high-speed tunnel are presented.
Date: September 1948
Creator: Lindsey, W. F.; Stevenson, D. B. & Daley, Bernard N.
Item Type: Refine your search to only Report
open access

The Aileron as an Aid to Recovery From the Spin

Description: From Introduction: "In order to afford a means of comparison and to obtain a clear understanding of the results, a study of the effects of normal angular deflections of the ailerons, with and against the spin, was included in the investigation. Ailerons deflected with the spin means that the ailerons are deflected with right aileron up and left aileron down in a right spin. The results of the investigation are discussed in this paper."
Date: September 1940
Creator: Neihouse, A. I.
Item Type: Refine your search to only Report
open access

Air-consumption parameters for automatic mixture control of aircraft engines

Description: From Introduction: "The purpose of this analysis was to investigate the use of function of intake-manifold temperature and pressure, exhaust back pressure, and engine speed in place of a ventri as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."
Date: September 1944
Creator: Shames, Sidney J.
Item Type: Refine your search to only Report
open access

Air-Consumption Parameters for Automatic Mixture Control of Aircraft Engines

Description: From Introduction: "The purpose of this analysis was to investigate the use of a function of intake-manifold pressure, exhaust back pressure, intake manifold temperature, and engine speed in place of a venturi as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."
Date: September 1, 1944
Creator: Shames, Sidney J.
Item Type: Refine your search to only Report
open access

Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation

Description: Report presenting 10 practical-construction models of sections of helicopter rotor blades tested in the NACA two-dimensional low-turbulence pressure tunnel at atmospheric pressure. Lift, drag, and pitching-moment characteristics of blades representing the present method of construction of the YR-4A helicopter were determined.
Date: September 1944
Creator: Tetervin, Neal
Item Type: Refine your search to only Report
open access

Airscrew Gyroscopic Moments

Description: "When flying in a turn or pulling out of a dive, the airscrew exerts a gyroscopic moment on the aircraft, In the case of airscrews with three or more blades, arranged symmetrically, the value of the gyroscopic moment is J(sub x) omega(sub x) omega(sub y), where J(sub x) denotes the axial moment of inertia about the axis of rotation of the airscrew, omega(sub x) the angular upeed of the airscrew about its axis, and omega (sub Y) the rotary speed of the whole aircraft about an axis parallel to th… more
Date: September 1946
Creator: Bock, G.
Item Type: Refine your search to only Report
open access

Altitude-chamber performance of British Rolls-Royce Nene II engine 1: standard 18.75-inch-diameter jet nozzle

Description: Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with a standard 18.75-inch-diameter jet nozzle. Results regarding the simulated flight performance and generalized performance across other altitude and pressure characteristics are provided.
Date: September 23, 1949
Creator: Barson, Zelmar & Wilsted, H. D.
Item Type: Refine your search to only Report
open access

Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes

Description: From Introduction: "The lift increments of different flap arrangements were determined by the method of reference 1 with a simple chord correction factor being applied. This procedure is somewhat similar in basic principles to the method of reference 2. The accuracy of the present method was determined by calculating by means of this method the lift and moment increments of flaps on 10 different finite wing-flap combinations for which wind-tunnel data were available."
Date: September 1944
Creator: Maggin, Bernard
Item Type: Refine your search to only Report
open access

Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System

Description: Report presenting an analysis of the effects of heat and compressibility in the flow through the internal systems of aircraft. Equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Date: September 1942
Creator: Becker, John V. & Baals, Donald D.
Item Type: Refine your search to only Report
open access

An analysis of longitudinal-control problems encountered in flight at transonic speeds with a jet-propelled airplane

Description: From Introduction: "This report presents an analysis based on flight and wind-tunnel test data directed toward the determination of the probable cause of the pitch-up. Wing pressure distribution and stability and control characteristics in the dive are also included."
Date: September 25, 1947
Creator: Brown, Harvey H.; Rolls, L. Stewart & Clousing, Lawrence A.
Item Type: Refine your search to only Report
open access

Analysis of measured pressures on airfoils at Mach numbers near 1

Description: Report presenting measured pressure over airfoils at Mach number 1, with subsonic velocities at the nose and supersonic velocities throughout the rear portion, are analyzed by comparison with calculations for similar cases. Results regarding the theoretical basis of approximation, comparison of Prandtl-Meyer flow with measurements, comparison of linear-velocity extrapolation with measurements, and effect of boundary layer upon airfoil pressures are provided.
Date: September 19, 1949
Creator: Habel, Louis W. & Miller, Mason F.
Item Type: Refine your search to only Report
open access

Analysis of Performance of a Jet Engine From Characteristics of Components 2: Interaction of Components as Determined From Engine Operation

Description: Report presenting an investigation of a method to analyze and to estimate performance of jet engines, which was applied to the study of the characteristics of a research turbojet engine built for the investigation. Results regarding the compressor performance, turbine performance, combustion chamber, and interaction of jet engine components are provided.
Date: September 1948
Creator: Goldstein, Arthur W.; Alpert, Sumner; Beede, William & Kovach, Karl
Item Type: Refine your search to only Report
open access

An Analysis of Supersonic Aerodynamic Heating With Continuous Fluid Injection

Description: From Introduction: "The aerodynamic heating problem assumes considerable importance at high-supersonic speeds. Sanger and Bredt (reference 1) have calculated the high-speed aerodynamic forces and equilibrium surface temperature at extremely high altitudes where the molecular mean free path is large (free-molecule-flow region) compared with a characteristic body dimension. The theoretical investigation of Lees (reference 2) on the stability of the laminar boundary layer in compressible flow ind… more
Date: September 29, 1949
Creator: Klunker, E. B. & Ivey, H. Reese
Item Type: Refine your search to only Report
open access

An analysis of the airspeeds and normal accelerations of Boeing S-307 airplanes in commercial transport operation

Description: From Introduction: "The present paper has been prepared to give the results of the analysis of the V-G records obtained from three Boeing S-307 airplanes operating in Caribbean region and the northern part of South America during the period from 1940 to 1944."
Date: September 1946
Creator: Peiser, A. M. & Walker, W. G.
Item Type: Refine your search to only Report
open access

An analysis of the airspeeds and normal accelerations of Douglas DC-3 airplanes in commercial transport operation

Description: From Introduction: "The present report is the second prepared to give the results of an analysis of V-G data from commercial transport airplanes. The present report is concerned with an analysis of data obtained with Douglas DC-3 airplanes flying over three transcontinental routes in the United States."
Date: September 1946
Creator: Peiser, A. M.
Item Type: Refine your search to only Report
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