National Advisory Committee for Aeronautics (NACA) - 43 Matching Results

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An analysis of a piston-type gas-generator engine

Description: From Introduction: "An analysis of an engine having a division of work such that the power of the reciprocating engine is just sufficient to drive the compressor is reported herein. This combination of a reciprocating-type internal-combustion engine that drives its own supercharging compressor and generates gas for further expansion through a turbine will be called a piston-type gas generator in this report."
Date: February 18, 1948
Creator: Tauschek, Max J. & Biermann, Arnold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending-Torsion Flutter Calculations Modified by Subsonic Compressibility Corrections

Description: From Summary: "A number of calculations of bending-torsion wing flutter are made at two Mach numbers, m=0 (incompressible case) and m=0.7, and results are compared. The air forces employed for the case of m=0.7 are based on Frazer's recalculation of Possio's results, which are derived on the assumption of small disturbances to the main flow. For ordinary wings of normal density and of low bending frequency in comparison with torsion frequency, the compressibility correction to the flutter speed… more
Date: December 18, 1945
Creator: Garrick, I. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of two fuels in bumblebee 18-inch ram jet incorporating rake-type flame holder

Description: Report presenting an investigation to determine the performance of a Bumblebee 18-inch ram jet with a rake-type flame holder was conducted using kerosene and propylene oxide as fuels. Experiments occurred at a range of pressure altitudes and ram-pressure ratios over the operable range of fuel-air ratios. Use of propylene oxide was found to improve the stability of combustion, increased the operable range of fuel-air ratios, and allowed ignition at high values of combustion-chamber-inlet velocit… more
Date: August 18, 1948
Creator: Wilcox, Fred A. & Howard, Ephraim M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades

Description: An analysis is presented of rim cooling of gas-turbine blades; that is, reducing the temperature at the base of the blade (wheel rim), which cools the blade by conduction alone. Formulas for temperature and stress distributions along the blade are derived and, by the use of experimental stress-rupture data for a typical blade alloy, a relation is established between blade life (time for rupture), operating speed, and amount of rim cooling for several gas temperatures. The effect of blade parame… more
Date: March 18, 1947
Creator: Wolfenstein, Lincoln; Meyer, Gene L. & McCarthy, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines, 4 - Calculated Temperature Distribution in the Trailing Part of a Turbine Blade Using Direct Liquid Cooling

Description: A theoretical analysis of the temperature distribution through the trailing portion of a blade near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the hot spot temperatures at the trailing edge and influence of design variables. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
Date: April 18, 1947
Creator: Brown, W. Byron & Monroe, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design Charts Relating to the Stalling of Tapered Wings

Description: An aid in airplane design, charts have been prepared to show the effects of wing taper, thickness ratio, and Reynolds number on the spanwise location of the initial stalling point. Means of improving poor stalling characteristics resulting from certain combinations of the variables have also been considered; additional figures illustrate the influence of camber increase to the wing tips, washout, central sharp leading edges, and wing-tip slots on the stalling characteristics. Data are included … more
Date: January 18, 1940
Creator: Soulé, H. A. & Anderson, R. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Aerodynamic Hysteresis on Critical Flutter Speed at Stall

Description: Memorandum presenting a theoretical analysis of the effect of aerodynamic hysteresis on stalling flutter. The results were applied to a given airfoil and correlation of the experimental and theoretical results was found possible by assuming that the angle of aerodynamic lag varies as the slope of the static-lift curve. It was shown that the phenomenon of stalling flutter can at least in some cases be explained on the basis of an aerodynamic lag or hysteresis effect.
Date: June 18, 1948
Creator: Mendelson, Alexander
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Amphibious Floats on the Power-Off Stability and Control Characteristics of a Twin-Engine Cargo Airplane

Description: Report presenting power-off wind tunnel tests of a scale model of a twin-engine cargo airplane equipped with amphibious floats. Longitudinal and lateral stability and control characteristics were investigated for three flap positions.
Date: January 18, 1943
Creator: Belsley, Steven E. & Jackson, Roy P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Centrifugal Force on Critical Flutter Speed on a Uniform Cantilever Beam

Description: Report presenting theoretical calculations made by means of semirigid-flutter theory to determine the effect of centrifugal force on the critical flutter speed of a uniform cantilever beam. Calculations are made on airfoils with fundamental bending frequencies up to 2000 radian per second. Centrifugal force can under certain conditions reduce the critical flutter speed.
Date: June 18, 1948
Creator: Mendelson, Alexander
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Engine-Operating Variables and Internal Coolants on Spark-Advance Requirements of a Liquid-Cooled Cylinder

Description: "Tests were conducted to determine the effect of engine-operating variables and internal coolants on spark-advance requirements of a single cylinder from a 12-cylinder liquid-cooled engine for maximum take-off power and maximum cruise economy. The effects of fuel-air ratio, engine speed, air flow (charge density), mixture temperature, and internal coolants on peak-power (optimum) spark advance were investigated. In addition, tests were conducted to determine the effect of spark advance on the k… more
Date: May 18, 1945
Creator: Pfender, John F.; Dudugjian, Carl & Lietzke, A. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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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Effects of Wing Flaps and Wing Duct Inlet on the Lift and Stalling Characteristics of a 1/4-Scale Partial-Span Model of the Republic XF-12 Airplane in the Langley 19-Foot Pressure Tunnel

Description: From Summary: "An investigation was conducted in the Langley 19-foot pressure tunnel to determine the lift, drag, pitching-moment and stalling characteristics of a 1/4 -scale partial-span model of the left wing of the Republic XF-12 airplane. The effects of a duct inlet, located between the nacelles at the leading edge of the wing, on those characteristics were also investigated. The Reynolds numbers for the investigation covered a range from 4,500,000 to 8,600,000. The results of the investiga… more
Date: November 18, 1946
Creator: Graham, Robert R.; Martina, Albert P. & Salmi, Reino J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of Flying Qualities of a P-47D-30 Airplane (AAF No. 43-3441) to Determine Longitudinal Stability and Control and Stalling Characteristics

Description: "Flight tests have been made to determine the longitudinal stability and control and stalling characteristics of the P-47.E-30 airplane. The teat results show the airplane to be unstable stick free in any power-on condition even at the most forward center-of-gravity position tested. At the rearward center-of-gravity position tested the airplane also had neutral to negative stick-fixed stability with power on. The characteristics in accelerated flight were acceptable at the forward center-of-gra… more
Date: February 18, 1948
Creator: Kraft, Christopher C., Jr.; Goranson, R. Fabien & Reeder, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Effect of Various Amounts of Aileron Droop on the Low-Speed Lateral-Control Characteristics of an Observation Airplane

Description: Report presenting tests of the low-speed lateral-control characteristics of an observation airplane with ailerons and spoilers in combination and with the spoilers disconnected and the ailerons used alone with various amounts of droop. The results indicated that in unstalled flight at low speeds and with flaps deflected, little or no aerodynamic benefit was derived by changing the lateral-control system from the aileron and spoiler combination to a normal aileron installation either with or wit… more
Date: August 18, 1943
Creator: Turner, William N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests of the High-Speed Performance of a P-51B Airplane (AAF No. 43-12105)

Description: Report discussing testing to check the improvement of 3 or 4 miles per hour in the maximum speed of the P-51B airplane as a result of sealing the wing-gun access doors and flap-spar lightening holes. Large variations in speed were observed during testing, so additional testing and analysis was carried out to determine the effects of various factors that were suspected of contributing to the inconsistency of the plane's performance.
Date: December 18, 1944
Creator: Voglewede, T. J. & Danforth, E. C. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/35-Scale Model of the Douglas XB-43 Airplane

Description: Spin tests have been performed in the Langley 20-foot free-spinning tunnel on a 1/35-scale model of the Douglas XB-43 airplane. The spin and recovery characteristics were determined for several loading conditions of the airplane. The effects of installing a dorsal fin and of installing a ventral fin were investigated. Emergency escape of the crew was simulated and the stick and rudder pedal forces necessary to effect recoveries on the airplane were determined.
Date: July 18, 1947
Creator: Snyder, Thomas L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fundamental effects of aging on creep properties of solution-treated low-carbon N-155 alloy

Description: A method is developed whereby the fundamental mechanisms are investigated by which processing, heat treatment, and chemical composition control the properties of alloys at high temperatures. The method used metallographic examination -- both optical and electronic --studies of x-ray diffraction-line widths, intensities, and lattice parameters, and hardness surveys to evaluate fundamental structural conditions. Mechanical properties at high temperatures are then measured and correlated with thes… more
Date: January 18, 1949
Creator: Frey, D. N.; Freeman, J. W. & White, A. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Further experiments on the flow and heat transfer in a heated turbulent air jet

Description: "Measurements have been made of the mean-total-head and mean-temperature fields in a round turbulent jet with various initial temperatures. The results show that the jet spreads more rapidly as its density becomes lower than that of the receiving medium, even when the difference is not sufficiently great to cause dynamic-pressure function. Rough analytical considerations have given the same relative spread. The effective "turbulent Prandtl number" for a section of the fully developed jet was fo… more
Date: August 18, 1947
Creator: Corrsin, Stanley & Uberoi, Mahinder S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The High-Speed Aerodynamic Effects of Modifications to the Wing and Wing-Fuselage Intersection of an Airplane Model with the Wing Swept Back 35 Degrees

Description: Memorandum presenting wind-tunnel tests at high subsonic Mach numbers conducted on a model of a pursuit airplane with a 45 degree sweptback wing. Tests were made to determine the effect of the wing trailing-edge angle, the fuselage contour at the wing-fuselage intersection, and an extension at the leading edge of the wing root.
Date: February 18, 1948
Creator: Boddy, Lee E. & Morrill, Charles P., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Speed Wind-Tunnel Tests of Semispan Horizontal Tails With Fabric-Covered and Metal-Covered Elevators for a Bomber Airplane

Description: "This report contains the results of tests of a full-scale semispan horizontal tail plane of a bomber airplane. The effects of fabric distortion on the aerodynamic characteristics of the elevator are determined by comparing the aerodynamic characteristics of a fabric-covered elevator with those of a metal-covered elevator. In addition, the results of cutting holes in the balance seal, the effect of fixing transition, the tab effectiveness both sealed and unsealed, and the section drag of this t… more
Date: December 18, 1944
Creator: Erickson, Albert L. & Nelson, Warren H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel. 2: The Effect of Constant-Chord Leading- and Trailing-Edge Flaps on the Low-Speed Characteristics of the Wing

Description: Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and a taper ratio of 0.50, equipped with leading- and trailing-edge flaps. The purpose of the tests was to determine the low-speed aerodynamic characteristics of the wing as affected by the separate or combined deflections of a full-span, constant-chord, leading-edge, plain flap and a partial-plan, constant-chord, trailing-edge flap of either the plain or split type. Results regarding the maximum li… more
Date: October 18, 1948
Creator: Johnson, Ben H., Jr. & Bandettini, Angelo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Performance of Typical Inlet Stage of Multistage Axial-Flow Compressor

Description: Memorandum presenting an investigation of a typical inlet stage of a multistage axial-flow compressor that was designed on the basis of an analysis of basic design variables. The stage, consisting of 19 rotor blades and 20 stator blades with 40 inlet guide vanes, had a hub-to-tip-radius ratio at the rotor inlet of 0.50 and a rotor-blade outside diameter of 14 inches. Results regarding the overall compressor performance, comparison of compressor performance with design, and rotor-row performance… more
Date: July 18, 1949
Creator: Burtt, Jack R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel: Part I - Basic Longitudinal Stability Characteristics, TED No. NACA DE308, Part 1, Basic Longitudinal Stability Characteristics, TED No. NACA DE308

Description: The stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane have been investigated over a Mach number range from 0.40 to 0.91. Results of the basic longitudinal tests of the complete model with undeflected control surfaces are given in the present report with a very limited analysis of the results.
Date: July 18, 1947
Creator: Kemp, William B., Jr.; Kuhn, Richard E. & Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel: Part II - Basic Lateral Stability Characteristics TED No. NACA DE308, Part 2, Basic Lateral Stability Charactistics, TED No. NACA DE308

Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The basic lateral stability characteristics of the complete model with undeflected control surfaces are presented in the present report with a very limited analysis of the results.
Date: July 18, 1947
Creator: Kemp, William B., Jr.; Goodson, Kenneth W. & Kuhn, Richard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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