National Advisory Committee for Aeronautics (NACA) - 30 Matching Results

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A general representation for axial-flow fans and turbines

Description: From Summary: "A general representation of fan and turbine arrangements on a single classification chart is presented which is made possible by a particular definition of the stage of an axial-flow fan or turbine. Several unconventional fan and turbine arrangements are indicated and the applications of these arrangements are discussed."
Date: June 1945
Creator: Perl, W. & Tucker, M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of Recovery Factors and Coefficients of Heat Transfer in a Tube for Subsonic Flow of Air

Description: Note presenting measurements of heat flow to air at subsonic velocities and substantially constant Reynolds number, which show that the heat-transfer coefficient is independent of the difference between the temperature of the heated wall and the adiabatic wall temperature. Recovery factors are measured at the pipe wall for adiabatic flow.
Date: June 1945
Creator: McAdams, William H.; Nicolai, Lloyd A. & Keenan, Joseph H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Net Heat of Combustion of AN-F-28 Aviation Gasolines

Description: "Experimental data on the heats of combustion and hydrogen contents of a number of aviation gasolines have been used in deriving a formula for computing net heat of combustion from (measured) gross heat of combustion. This formula appears to be sufficiently reliable for the purpose and has the advantage of making hydrogen determinations unnecessary. The data on heats of combustion are presented in tabular form, and in graphs showing the relation between net heat of combustion and (1) hydrogen c… more
Date: June 1945
Creator: Jessup, R. S. & Cragoe, C. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Control-Surface Characteristics 22: Medium and Large Aerodynamic Balances of Two Nose Shapes and a Plain Overhang Used With a 0.20-Airfoil-Chord Flap on an NACA 0009 Airfoil

Description: "Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an el… more
Date: June 1945
Creator: Riebe, John M. & McKinney, Elizabeth G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of fabric deflection at high speeds on the aerodynamic characteristics of the horizontal tail surface of an SB2D-1 airplane

Description: Report presenting an investigation of a full-scale horizontal tail surface to determine the elevator-fabric deflection at high speeds and the aerodynamic effects of the fabric deflection. Two fabric-covered elevators differing only in rib spacing and a solid wooden elevator were tested. Results regarding fabric deflection and aerodynamic characteristics are provided.
Date: June 1945
Creator: Schueller, Carl F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of elevator-profile modifications and trailing-edge strips on elevator hinge-moment and other aerodynamic characteristics of a full-scale horizontal tail surface

Description: Report presenting results of a full-scale horizontal tail surface made to determine the effect of elevator-profile modifications and trailing-edge strips on the elevator hinge-moment characteristics for elevators having fixed plan plan form and constant balance. Results regarding the basic data with the metal elevator, effect of trailing-edge angle, effect of nose shape, and effects of trailing-edge strips are provided.
Date: June 1945
Creator: Schueller, Carl F.; Korycinski, Peter F. & Strass, H. Kurt
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of various carburetor throttle settings on the flow characteristics at the outlet of a supercharger inlet elbow

Description: Report presenting an investigation to determine the effect of varying the carburetor throttle settings on the flow characteristics at the outlet of the supercharger inlet elbow. Air flow tests were made at several carburetor throttle settings ranging from open to closed. Results regarding distortion and turbulence are provided.
Date: June 1945
Creator: Moses, Jason J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The development and application of high-critical-speed nose inlets

Description: From Summary: "An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum from the standpoint of critical speed has shown that marked similarity exists between the nondimensional profiles of inlets which have widely different proportions and critical speeds. With the nondimensional similarity of such profiles established, the large differences in the critical speeds of these nose inlets must be a function of their proportions. An investigation was underta… more
Date: June 8, 1945
Creator: Baals, Donald D.; Smith, Norman F. & Wright, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Nitrous Oxide Supercharging of an Aircraft-Engine Cylinder

Description: Report discussing tests to determine the performance of an aircraft engine cylinder using nitrous oxide to provide additional supercharging. The test results of injecting it as a gas and calculated results of injecting it as a liquid are described.
Date: June 26, 1945
Creator: Tauschek, Max J.; Corrington, Lester C. & Huppert, Merle C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Evaluation of the Induced-Velocity Field of an Idealized Helicopter Rotor

Description: Report presenting a concept of a simplified vortex system of a rotor wake in order to obtain a formula for the normal component of induced velocity along the fore-and-aft diameter of the rotor disk of a helicopter rotors.
Date: June 1945
Creator: Coleman, Robert P.; Feingold, Arnold M. & Stempin, Carl W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Inlet Pressure and Temperature on the Efficiency of a Single Stage Impulse Turbine Having an 11.0-Inch Pitch-Line Diameter Wheel

Description: Efficiency tests have been conducted on a single-stage impulse engine having an 11-inch pitch-line diameter wheel with inserted buckets and a fabricated nozzle diaphragm. The tests were made to determine the effect of inlet pressure, Inlet temperature, speed, and pressure ratio on the turbine efficiency. An analysis is presented that relates the effect of inlet pressure and temperature to the Reynolds number of the flow. The agreement between the analysis and the experimental data indicates tha… more
Date: June 1945
Creator: Gabriel, David S.; Carman, L. Robert & Trautwein, Elmer E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of the Skis on the Power-Off Stability Characteristics of a Twin-Engine Cargo Airplane

Description: Report discussing the results of power-off wind tunnel tests of a twin-engine cargo airplane equipped with wheel skis. Stability characteristics are described for two flap positions and three ski positions. The effect of fairing the main skis in the retracted position on the drag coefficient is also described.
Date: June 18, 1945
Creator: Wong, Park Y.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight investigation at high speeds of flow conditions over an airplane wing as indicated by surface tufts

Description: Report presenting flight tests with a P-47D airplane to determine the flow characteristics on a section of the upper surface of the wing. The behavior of the wool tufts used to measure these characteristics was determined from motion pictures. The results indicated that the flow remained smooth over the test panel until the critical Mach number was exceeded by 0.08 at lift coefficient 0.10 and by 0.05 at a lift coefficient of 0.50.
Date: June 1945
Creator: Wood, Clotaire & Zalovcik, John A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived From Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)

Description: Two-dimensional data were obtained in Mach range of from 0.40 to 0.94 and Reynolds Number range of (3.4 - 4.2) X 10 Degrees. Results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections. Effects of jet boundaries, Reynolds Number, and Data presented are free from jet-boundary and humidity effects.
Date: June 1945
Creator: Ferri, Antonio
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation of Methods for Computing Drag From Wake Surveys at High Subsonic Speeds

Description: Report discusses graphs of constants meant to be used with a knowledge of maximum total head loss, static-pressure decrement, and integral of total-head loss across the wake of an airfoil to determine the section profile-drag coefficient. Computations of free-stream Mach numbers for certain assumed types of total-pressure distribution in the wake are provided to compare theoretical drag coefficients as determined by other equations based on the momentum method. While some disagreements are foun… more
Date: June 1945
Creator: Heaslet, Max A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination From Flight Tests of Thrust Coefficients for 10 Full-Scale Airplanes in the Gliding Condition With Engine Idling

Description: "Typical thrust and torque coefficients and increments, due to the propeller, in the ratio of the dynamic pressure at the tail to the free-stream dynamic pressure are presented for 10 full-scale airplanes. Calculations indicate that an error of about 2 percent mean aerodynamic chord appears possible in determining the neutral point from wind-tunnel tests or a model in the gliding condition if the propeller is operated at zero thrust rather than at the values of thrust coefficient indicated by t… more
Date: June 1945
Creator: Talmage, Donald B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Additional Investigation of the High-Speed Lateral-Control Characteristics of Spoilers

Description: Report presenting an investigation of the characteristics of partial-span spoilers located at 0.75 of the chord on an NACA 66-series tapered wing, especially at high speeds. The effect of small spoiler projections was found to increase with an increase in speed until the critical Mach number was exceeded.
Date: June 1945
Creator: Laitone, Edmund V. & Summers, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Estimation of the Performance and Longitudinal Stability and Control of a Lifting-Body Type of Cargo Airplane From Tests of Simplified Models

Description: Report comparing the drag of an airplane with a conventional body with that of an airplane carrying cargo in a detachable airfoil-shaped body. Information about the performance, longitudinal stability, and control characteristics of a lifting-body cargo airplane is also provided and compared with a conventional cargo airplane.
Date: June 1945
Creator: Feigenbaum, D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects on Low-Speed Spray Characteristics of Various Modifications to a Powered Model of the Boeing XPBB-1 Flying Boat

Description: Report presenting tests of a powered model of the Boeing XPBB-1 flying boat in order to observe the effects of trim and powered propellers, of lengths of forebody and afterbody, and of various spray strips on the low-speed spray characteristics. The effects of powering the propellers were to lower the trim and to pick up spray that would not strike the propeller disks when the propellers were windmilling. Results regarding the effects of trim and powered propellers, effect of length of forebody… more
Date: June 1945
Creator: King, Douglas A. & Mas, Newton A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Internal Coolants on the Knock-Limited Performance of a Liquid-Cooled Multicylinder Aircraft Engine With a Compression Ratio of 6.0

Description: Report discussing the effect of internal coolants on the knock-limited performance of a liquid-cooled multicylinder aircraft engine. Both water and water-ethanol mixtures were tested at several carburetor-air temperatures. Fuel-nozzle injection of the coolant was found to be more effective than injection through intake-manifold spray jets.
Date: June 1945
Creator: Nelson, R. Lee; Harries, Myron L. & Brun, Rinaldo J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Column and plate compressive strengths of aircraft structural materials: 17S-T aluminum-alloy sheet

Description: From Summary: "Column and plate compressive strengths of 17S-T aluminum-alloy sheet were determined both within and beyond the elastic range from tests of thin-strip columns and from local-instability tests of formed Z- and channel-section columns. These tests are part of an extensive research investigation to provide data on the structural strengths of various aircraft materials. Results are presented in the form of curves and charts that may be used in the design and analysis of aircraft stru… more
Date: June 1945
Creator: Heimerl, George J. & Roy, J. Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Suitability of 18 Aromatic Amines for Overwater Storage When Blended With Aviation Gasoline

Description: Report discussing testing of aromatic amines as antiknock additives, and more specifically the suitability of overwater storage for these fuel blends. 12 aromatic amines of three different concentrations at two temperatures were measured. The chemical properties of the most promising fuel blends are described in more detail and correlations were noted.
Date: June 20, 1945
Creator: Goodman, Irving A. & Howard, J. Nelson
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Backflow Phenomenon in Centrifugal Superchargers

Description: Report presenting an investigation to determine the nature and extent of the reversal of flow, which occurs at the inlet of centrifugal superchargers over a considerable portion of the operating range. Results regarding lampback patterns, tuft studies, backflow surveys, and effect of impeller tip speed on backflow are provided.
Date: June 1945
Creator: Benser, William A. & Moses, Jason J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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