National Advisory Committee for Aeronautics (NACA) - 74 Matching Results

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Subsonic flow over thin oblique airfoils at zero lift

Description: A previous report gave calculations for the pressure distribution over thin oblique airfoils at supersonic speed. The present report extends the calculations to subsonic speeds. It is found that the flows again can be obtained by the superposition of elementary conical flow fields. In the case of the swept-back wing the pressure distributions remain qualitatively similar at subsonic and supersonic speeds. Thus a distribution similar to the Ackeret type of distribution appears on the root sectio… more
Date: May 1947
Creator: Jones, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical motions of hydrofoil systems

Description: "Results are presented of an investigation that has been undertaken to develop theoretical methods of treating the motions of hydrofoil systems and to determine some of the important parameters. Variations of parameters include three distributions of area between the hydrofoils, two rates of change of downwash angle with angle of attack, three depths of immersion, two dihedral angles, two rates of change of lift with immersion, three longitudinal hydrofoil spacings, two radii of gyration in pit… more
Date: May 9, 1947
Creator: Imlay, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Engine Skew on Directional and Lateral Control Characteristics of Single-Engine Airplanes

Description: Report discussing an investigation on the effect of engine skew on the directional and lateral control characteristics of a single-engine airplane with a single-rotating propeller. The estimated and test results showed an advantage to skewing the propeller, as it assists with overcoming inadequate rudder control in power-on flight and aileron control, especially with flaps deflected.
Date: May 16, 1947
Creator: Wallace, Arthur R. & Comenzo, Raymond J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Axial-Flow Fan and Compressor Rotors Designed for Three-Dimensional Flow

Description: "An investigation has been conducted to determine whether three-dimensional flows may be utilized in axial-flow fan and compressor rotors so that the spanwise load distribution may be varied to obtain high pressure rise. Two rotors, one with approximately uniform and one with solid-body downstream tangential-velocity distributions, were designed and tested at the design blade angle" (p. 1).
Date: May 2, 1947
Creator: Kahane, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Description: "A Douglas C-74 airplane, during a test dive at about 0.525 Mach number, experienced uncontrollable longitudinal oscillations sufficient to cause shedding of the outer wing panels and the subsequent crash of the airplane. Tests of a section of the horizontal tail plane from a C-74 airplane were conducted in the Ames 16-foot high-speed wind tunnel to investigate the possibility of the tail as a contributing factor to the accident. The results of the investigations of fabric-covered elevators in … more
Date: May 6, 1947
Creator: Perone, Angelo & Berthold, Cecil L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines 6 - Computed Temperature Distribution Through Cross Section of Water-Cooled Turbine Blade

Description: "A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to… more
Date: May 1, 1947
Creator: Livingood, John N. B. & Sams, Eldon W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Rocket Power Plants Based on Nitric Acid and their Specific Propulsive Weights

Description: "Two fields are reserved for the application of rocket power plants. The first field is determined by the fact that the rocket power plant is the only type of power plant that can produce thrust without dependence upon environment. The second field is that in which the rocket power plant proves itself the most suitable as a high-power drive in free competition with other types of power plants" (p. 1).
Date: May 1947
Creator: Zborowski, Helmut
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Acceleration Measurements During Landing in Rough Water of a 1/7-Scale Dynamic Model of Grumman XJR2F-1 Amphibian - Langley Tank Model 212: TED No. NACA 2378

Description: From Summary: "Tests of a 1/7 size model of the Grumman XJR2F-1 amphibian were made in Langley tank no.1 to examine the landing behavior in rough water and to measure the normal and angular accelerations experienced by the model during these landings. All landings were made normal to the direction of wave advance, a condition assumed to produce the greatest accelerations. Wave heights of 4.4 and 8.0 inches (2.5 and 4.7 ft, full size) were used in the tests and the wave lengths were varied betwe… more
Date: May 6, 1947
Creator: Land, Norman S. & Zeck, Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Spinning Tunnel Tests of a 1/24-Scale Model of the Grumman XTB3F-1 Airplane, TED No. NACA DE304

Description: In accordance with a request of the Bureau of Aeronautics, Navy Department, tests were performed in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 1/24 scale model of the Grumman XTB3F-1 airplane. The airplane is a two-place, midwing torpedo bomber equipped with a tractor propeller and an auxiliary jet engine. The effect of control setting and movement on the erect and inverted spin and recovery characteristics of the model were determined for t… more
Date: May 9, 1947
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effectiveness at High Speeds of a 20-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil

Description: "An analysis has been made of the lift control effectiveness of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section from section lift-coefficient data obtained at Mach numbers from 0.3 to 0.875. In addition, the effectiveness of the plain flap as a lift-control device has been compared with the corresponding effectiveness of both a spoiler and a dive-recovery flap on the NACA 65-210 airfoil section. The analysis indicates that the plain trailing-edge flap employed on … more
Date: May 6, 1947
Creator: Stivers, Louis S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Compressor of XJ-41-V Turbojet Engine 2 - Static-Pressure Ratios and Limitation of Maximum Flow at Equivalent Compressor Speed of 8000 RPM

Description: "At the request of the Air Material Command, Army Air Forces, an investigation was conducted by the NACA Cleveland laboratory to determine the performance characteristics of the compressor of the XJ-41-V turbojet engine. This report is the second in a series presenting the compressor performance and analysis of flow conditions in the compressor. The static-pressure variation in the direction of flow through the compressor and the location and the cause of the maximum flow restriction at an equi… more
Date: May 6, 1947
Creator: Dildine, Dean M. & Arthur, W. Lewis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Spin and Recovery Characteristics of the Curtiss-Wright XP-87 Airplane

Description: "The spin and recovery characteristics of the Curtiss-Wright XP-87 airplane, as well as the spin-recovery parachute requirements, the control forces that would be encountered in the spin, and the best method for the crew to attempt an emergency escape, are presented in this report. The characteristics were estimated rather than determined by model tests because the XP-87 dimensional and mass characteristics were considered to be noncritical and because data were available from model tests of se… more
Date: May 26, 1947
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Landing Characteristics in Waves of Three Dynamic Models of Flying Boats

Description: Powered models of three different flying boats were landed in oncoming wave of various heights and lengths. The resulting motions and acceleration were recorded to survey the effects of varying the trim at landing, the deceleration after landing, and the size of the waves. One of the models had an unusually long afterbody. The data for landing with normal rates of deceleration indicated that the most severe motions and accelerations were likely to occur at some period of the landing run subsequ… more
Date: May 7, 1947
Creator: Benson, James M.; Havens, Robert F. & Woodward, David R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fundamentals of the Control of Gas-Turbine Power Plants for Aircraft, Part 3: Control of Jet Engines

Description: "The basic principles of the control of TL engines are developed on the basis of a quantitative investigation of the behavior of these behavior under various operating conditions with particular consideration of the simplifications permissible in each case. Various possible means of control of jet engines are suggested and are illustrated by schematic designs" (p. 1).
Date: May 1947
Creator: Kühl, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compilation of Test Data on 111 Free-Spinning Airplane Models Tested in the Langley 15-Foot and 20-Foot Free-Spinning Tunnels

Description: "A compilation of free-spinning-airplane model data on the spin and recovery characteristics of 111 airplanes is presented. These data were previously published in separate memorandum reports and were obtained from free-spinning tests in the Langley 15-foot and the Langley 20-foot free-spinning tunnels. The model test data presented include the steady-spin and recovery characteristics of each model for various combinations of aileron and elevator deflections and for various loadings and dimensi… more
Date: May 15, 1947
Creator: Malvestuto, Frank S., Jr.; Gale, Lawrence J. & Wood, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effectiveness at High Speeds of a 20-Percent-Chord Plain Trailing-Edge Flap on the NACA 65-210 Airfoil Section

Description: "An analysis has been made of the lift-control effectiveness of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section from section lift-coefficient data obtained at Mach numbers from 0.3 to 0.875. In addition, the effectiveness of the plain flap as a lift-control device has been compared with the corresponding effectiveness of both a spoiler and a dive-recovery flag on the INCA 65-210 airfoil section" (p. 1).
Date: May 6, 1947
Creator: Stivers, Louis S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling Characteristics of the V-1650-7 Engine, 1, Coolant-Flow Distribution, Cylinder Temperatures, and Heat Rejections at Typical Operating Conditions

Description: From Summary: "An investigation was conducted to determine the coolant-flow distribution, the cylinder temperatures, and the heat rejections of the V-1650-7 engine . The tests were run a t several power levels varying from minimum fuel consumption to war emergency power and at each power level the coolant flows corresponded to the extremes of those likely to be encountered in typical airplane installations, A mixture of 30-percent ethylene glycol and 70-percent water was used as the coolant. T… more
Date: May 23, 1947
Creator: Povolny, John H. & Bogdan, Louis J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Further investigation of NACA 4-(5)(08)-03 two-blade propeller at high forward speeds

Description: Report presenting tests of an NACA 4-(5)(08)-03 two-blade propeller in the 8-foot high-speed tunnel for blade angles of 45 and 60 degrees extending the Mach number range from that of previous tests of the propeller up to Mach number 0.913. When the forward speed was increased from a low value to a forward Mach number of 0.90, the loss in peak efficiency was found to be not more than 47 percent.
Date: May 26, 1947
Creator: Carmel, Melvin M. & Robinson, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Initial Test in the Transonic Range of Four Flutter Airfoils Attached to a Freely Falling Body

Description: Report presenting the results of testing in the transonic range of four flutter airfoils attached to a freely falling body. Failures of the airfoils were metered and recorded in order to determine the Mach numbers and altitudes of failure.
Date: May 5, 1947
Creator: Barmby, J. G. & Clevenson, S. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Location of Detached Shock Wave in Front of a Body Moving at Supersonic Speeds

Description: "It is shown that for velocities slightly in excess of sonic, the position of detached shock wave located in front of a given body at zero angle of attack may be estimated theoretically to a reasonable degree of accuracy. In case of bodies of revolution the result was simple, but for two-dimensional bodies, pressure coefficient varies with Mach number, and slight difficulty appears. Theory developed compares favorably with available experimental data" (p. 1).
Date: May 6, 1947
Creator: Laitone, Edmund V. & Pardee, Otway O'M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine II: performance with water injection at compressor inlet

Description: Report presenting testing of a standard turbojet engine by water injection at the inlet of the axial-flow compressor in the altitude wind tunnel. Engine performance at 7600 rpm was obtained over a wide range of water-air-pressure ratios and ram-pressure ratios. Results regarding the engine-component performance are also provided.
Date: May 19, 1947
Creator: Dietz, Robert O. & Fleming, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of Two Full-Scale Propellers to Determine the Effect of Swept-Back Blade Tips on Propeller Aerodynamic Characteristics

Description: Report presenting an investigation of two 10-foot-diameter three-blade propellers to determine the effect of swept-back blade tips on propeller aerodynamic characteristics. Results regarding the effect of swept-back tips on maximum efficiency and constant-power propeller operation are provided.
Date: May 12, 1947
Creator: Evans, Albert J. & Klunker, E. Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of a Fuselage and Various High-Lift and Stall-Control Flaps on Aerodynamic Characteristics in Pitch of an NACA 64-Series 40 Degree Swept-Back Wing

Description: Report presenting wind-tunnel testing to determine the low-speed lift, drag, and pitching-moment characteristics of a 40 degree sweptback wing with high-lift and stall-control flaps and a fuselage with a fineness ratio of 10.2 to 1. Low, medium, and high-wing-fuselage combinations were tested at high Reynolds numbers. Results regarding the high-lift and stall-control flaps and wing-fuselage combinations are provided.
Date: May 26, 1947
Creator: Conner, D. William & Neely, Robert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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