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1,535 Matching Results
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Wind-Tunnel Tests of a 0.182-Scale Model of an F4U-1 Airplane with External Stores
Tests were made in the Langley 7- by 10-foot tunnel on a 0.182-scale model of an F4U-1 airplane with external stores. This paper is concerned mainly with presenting the data obtained in this investigation and with a comparison of some of these data with flight-test results determining the feasibility of estimating flight buffet Mach number from tunnel data. The results of this investigation indicate that the incremental drag coefficient due to external stores may be used to estimate the maximum Mach number that the F4U-1 airplane may reach in flight when it is equipped with external stores. This estimation is conservative for the five configurations investigated by mounts varying from 0 to 10 percent of the flight limit Mach number. The free-stream tunnel Mach number corresponding to sonic flow over the lower surface of the wing in the region of the store is a good indication of the lower limit of buffet in flight of the F4U-1 airplane when equipped with external stores. The fluctuations of total pressure over the horizontal tail are not sufficiently large (maximum of 1 percent q(sub o) to cause buffeting of the airplane.
Date:
June 5, 1947
Creator:
Silvers, H. Norman & Spreemann, Kenneth P.
Object Type:
Report
System:
The UNT Digital Library
Performance Investigation of TG-180 Combustor: 1 - Instrumentation, Altitude Operational Limits and Combustion Efficiency
A brief investigation has been made of the performance of a single combustor of the TG-180 turboJet engine to determine (a) the altitude operational limits of the engine for two fuels (AN-F-32 and AN-F-28), (b) combustion efficiencies at various simulated conditions of altitude and engine speeds, (c) combustion-outlet temperature distribution for several altitudes at constant engine speed, and (d) the combustor total pressure drop The limits with AN-83-F-32 fuel were found to be approximately 60,000 feet for an engine speed of 6000 rpm and approximately 38,000 feet for an engine speed of 1000 rpm. The results indicated that the altitude operational limits with AN-F-32 fuel are higher over the largest part of the engine-speed range than with AN-F-28 fuel, A combination efficiency of 22 percent was obtained at rated engine speed (7600 rpm) and an altitude of 20,000 feet with AN-F-32 fuel. A change in altitude from 20,000 tm 60,000 feet showed a 20-percent decrease in combustion efficiency while the engine was operating at 760G rpm whereas, at an engine speed of 4000 rpm a change of altitude from 10,000 to 40,000 feet showed a 52-percent decrease in combustion efficiency .
Date:
January 13, 1947
Creator:
Zettle, Eugene V. & Cook, William P.
Object Type:
Report
System:
The UNT Digital Library
Performance of Compressor XJ-41-V Turbojet Engine 1 - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM
From Summary: "At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The complete compressor was mounted on a collecting chamber having an annular air-flow passage simulating the burner annulus of the engine and was driven by an electric motor. The compressor was extensively instrumented to determine the overall performance of the compressor, the characteristic performance of each of the compressor components, the state of the air stream in the simulated burner annulus, and the operation of the compressor bearings."
Date:
January 17, 1947
Creator:
Ginsburg, Ambrose & Creagh, John W. R.
Object Type:
Report
System:
The UNT Digital Library
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
"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 equivalent speed of 8000 rpm are presented" (p. 1).
Date:
May 6, 1947
Creator:
Dildine, Dean M. & Arthur, W. Lewis
Object Type:
Report
System:
The UNT Digital Library
An Analysis of the Full-Floating Journal Bearing
"An analysis of the operating characteristics of a full-floating bearing - a bearing in which a floating sleeve is located between the journal and bearing surfaces - is presented together with charts - from which the performance of such bearings may be predicted. Examples are presented to illustrate the use of these charts and a limited number of experiments conducted upon a glass full-floating bearing to verify some results of the analysis are reported. The floating sleeve can operate over a wide range of speeds for a given shaft speed, the exact value depending principally upon the ratio of clearances and upon the ratio of radii of the bearing" (p. 1).
Date:
January 28, 1947
Creator:
Shaw, M. C. & Nussdorfer, T. J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Calculations and Experimental Investigations on the Feed-Power Requirement of Airplanes With Boundary-Layer Control
"Calculations and test results are given about the feed-power requirement of airplanes with boundary-layer control. Curves and formulas for the rough estimate of pressure-loss and feed-power requirement are set up for the investigated arrangements which differ structurally and aerodynamically. According to these results the feed power for three different designs is calculated at the end of the report" (p. 1).
Date:
September 1947
Creator:
Krüger, W.
Object Type:
Report
System:
The UNT Digital Library
Ditching Tests of a 1/18-Scale Model of the Navy XP4M-1 Airplane in Langley Tank No. 2 and on an Outdoor Catapult, TED No. NACA 2362
From Summary: "Tests with a dynamically similar model of the Navy XP4M-1 airplane were made to determine the best way to land the airplane in calm and rough water, to determine its probable ditching performance, and to determine practicable modifications which could be incorporated in the design of the airplane that would improve its ditching characteristics. The results were obtained by making visual observations, by recording longitudinal decelerations ,and by taking motion pictures of the landings. A list of conclusions from the test results is included."
Date:
March 10, 1947
Creator:
Fisher, Lloyd J. & Hoffman, Edward L.
Object Type:
Report
System:
The UNT Digital Library
Pressure-Distribution Measurements on a Straight and on a 35 Degree Swept-Back Tapered Wing
"The spanwise lift-distribution measurements in straight air flow on a straight and a 35 deg swept-back tapered wing (NACA airfoil section 0012) are compared with theory for two angles of attack each (alpha approx. 6 deg and alpha approx. 12 deg) in the unstalled range of flow. The complete pressure distribution for the greater of the two angles is indicated" (p. 1).
Date:
January 1947
Creator:
Thiel, A. & Weissinger, J.
Object Type:
Report
System:
The UNT Digital Library
Test Report on Measurements on a Series of Tapered Wings of Small Aspect Ratio (Trapezoidal Wing with Fuselage)
"This is the second of a series of six reports dealing with three- and six-component measurements on the tapering series at small aspect ratio. The present report concerns the trapezoidal wing with fuselage" (p. 1).
Date:
July 1947
Creator:
Lange & Wacke
Object Type:
Report
System:
The UNT Digital Library
Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms July 22, 1946 to July 23, 1946 at Orlando, Florida
"The results obtained from measurements of gust and draft velocities within thunderstorms for the period July 22, 1946 to July 23, 1946 at Orlando, Florida, are presented herein. These data are summarized in tables I and II, respectively, and are of the type presented in reference 1 for previous flights. Inspection of photo-observer records for the flights indicated that no data on ambient air temperature variations within thunderstorms were obtained" (p. 1).
Date:
March 10, 1947
Creator:
Tolefson, H. B.
Object Type:
Report
System:
The UNT Digital Library
Spin and Recovery Characteristics of the Curtiss-Wright XP-87 Airplane
"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 several similar airplanes. The study indicated that the recovery characteristics of the airplane will be satisfactory for all loadings if the controls are reversed fully and rapidly" (p. 1).
Date:
May 26, 1947
Creator:
Berman, Theodore
Object Type:
Report
System:
The UNT Digital Library
Fundamentals of the Control of Gas-Turbine Power Plants for Aircraft, Part 1: Standardization of the Computations Relating to the Control of Gas-Turbine Power Plants for Aircraft by the Employment of the Laws of Similarity
"It will be shown that by the use of the concept of similarity a simple representation of the characteristic curves of a compressor operating in combination with a turbine may be obtained with correct allowance for the effect of temperature. Furthermore, it becomes possible to simplify considerably the rather tedious investigations of the behavior of gas-turbine power plants under different operating conditions. Characteristic values will be derived for the most important elements of operating behavior of the power plant, which will be independent of the absolute values of pressure and temperature" (p. 1).
Date:
April 1947
Creator:
Kühl, H.
Object Type:
Report
System:
The UNT Digital Library
Effects of Compressibility on the Flow Past Thick Airfoil Sections
"Six, 3-inch-chord symmetrical airfoil sections having systematic variations in thickness and thickness location were tested at Mach numbers near flight values for propeller-shank sections. The tests, the results of which are presented in the form of schlieren photographs of the flow past each model and pressure-distribution charts for two of the model, were performed to illustrate the effects of compressibility on the flow past thick symmetrical airfoil sections. Representative flow photographs indicated that at Mach numbers approximately 0.05 above the critical Mach number a speed region was reached in which the flow oscillated rapidly and the separation point and the location of the shock wave were unstable" (p. 1).
Date:
January 30, 1947
Creator:
Daley, Bernard N. & Humphreys, Milton D.
Object Type:
Report
System:
The UNT Digital Library
A Low-Speed Investigation of a Fuselage-Side Air Inlet for use at Transonic Flight Speeds
"A low-speed investigation in the Langley propeller-research tunnel of annular air inlets designed to avoid compression shocks and attendant boundary-layer separation on the fuselage ahead of the inlets at transonic flight speeds by maintaining substream flow velocities on the fuselage nose was reported in NACA RM No. L6J04. In the present investigation, one of the original annular inlets was converted by the installation of a canopy and a nose-wheel fairing into a twin side inlet in order to study problems involved in applying such an inlet to a fighter-type airplane. Extensive measurements of pressures on the surface of the model and surveys of the internal flow were conducted at angles of attack of 0 degrees, 3 degrees, and 6 degrees over a wide range of inlet-velocity ratio" (p. 1).
Date:
April 9, 1947
Creator:
Nichols, Mark R. & Goral, Edwin B.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections
Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.
Date:
November 14, 1947
Creator:
Loftin, Laurence K., Jr. & Cohen, Kenneth S.
Object Type:
Report
System:
The UNT Digital Library
Landing Characteristics in Waves of Three Dynamic Models of Flying Boats
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 subsequent to the initial impact.
Date:
May 7, 1947
Creator:
Benson, James M.; Havens, Robert F. & Woodward, David R.
Object Type:
Report
System:
The UNT Digital Library
Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift
"On the basis of a recently developed theory for sweptback wings at supersonic velocities, equations are derived for the wave drag of sweptback tapered wings with thin symmetrical double-wedge sections at zero lift. Calculations of section wave-drag distributions and wing wave drag are presented for families of tapered plan forms. Distributions of section wave drag along the span of tapered wings are, in general, very similar in shape to those of untapered plan forms" (p. 1).
Date:
October 6, 1947
Creator:
Margolis, Kenneth
Object Type:
Report
System:
The UNT Digital Library
Lift and Drag of Wings with Small Span
The lift coefficient of a wing of small span at first shows a linear increase for the increasing angle of attack, but to a lesser degree then was to be expected according to the theory of the lifting line; thereafter the lift coefficient increases more rapidly than linearity, as contrasted with the the theory of the lifting line. The induced drag coefficient for a given lift coefficient, on the other hand, is obviously much smaller than it would be according to the theory. A mall change in the theory of the lifting line will cover these deviations.
Date:
August 1947
Creator:
Weinig, F.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the Trim Characteristics of a 1/20-Scale Model of the Fleetwings XBTK-1 Airplane over a Wide Range of Angles of Attack
"Tests of a 1/20-scale model of the Fleetwings XBTK-1 airplane have been performed in the Langley 15-foot free-spinning tunnel to determine the trim tendencies of the airplane at attitudes above the stall. The results of the tests indicated that the model would trim longitudinally only in the normal range of angles of attack and that the yaw trim tendencies for such longitudinal trim conditions were normal. Although wide oscillations in yaw were noted for some conditions, they occurred at angles of attack larger than those indicated as possible for longitudinal trim and spin equilibrium" (p. 1).
Date:
March 5, 1947
Creator:
Stone, Ralph W., Jr. & Berman, Theodore
Object Type:
Report
System:
The UNT Digital Library
On the Problems of Chaplygin for Mixed Sub-and Supersonic Flows
"There are investigated the problems of the flow of a supersonic jet out of a vessel with plane side walls and the problem of the supersonic flow about a wedge when there is a zone of local subsonic velocities ahead of the wedge" (p. 1).
Date:
June 1947
Creator:
Frankl, F.
Object Type:
Report
System:
The UNT Digital Library
Concerning the Velocity of Evaporation of Small Droplets in a Gas Atmosphere
"The evaporation velocity of liquid droplets under various conditions is theoretically calculated and a number of factors are investigated which are neglected in carrying out the fundamental equation of Maxwell. It is shown that the effect of these factors at the small drop sizes and the small weight concentrations ordinarily occurring in fog can be calculated by simple corrections. The evaporation process can be regarded as quasi-stationary in most cases" (p. 1).
Date:
August 1947
Creator:
Fuchs, N.
Object Type:
Report
System:
The UNT Digital Library
Measurements in Flight of the Flying Qualities of a Chance Vought F4U-4 Airplane: TED No. NACA 2388
From Summary: "The results of flight tests to determine flying qualities of a Chance Vought F4U-4 airplane are presented and discussed herein. In addition to comprehensive measurements at low altitude (about 8000 ft), tests of limited scope were made at high altitude (about 25,000 ft)."
Date:
March 20, 1947
Creator:
Liddell, Charles J., Jr.; Reynolds, Robert M. & Christofferson, Frank E.
Object Type:
Report
System:
The UNT Digital Library
Supersonic Wave Drag of Sweptback Tapered Wings at Zero Lift
An analysis has been made of airfoil data taken on several NACA 16-series propeller airfoils from tests of 5-inch-chord models in the Langley 24 inch high-speed tunnel and l2-inch-chord models in the Langley 8 foot high-speed tunnel, This analysis has shown that the combined effects of Reynolds number changes and variations in airfoil characteristics resulting from differences in models and tunnels are such that when 5 inch-chord and l2-inch-chord data are applied to full-scale propeller design at or near the design condition, differences of less than 1 percent in efficiency will be involved.
Date:
June 11, 1947
Creator:
Margolis, Kenneth
Object Type:
Report
System:
The UNT Digital Library
Force and Pressure-Distribution Measurements on a Rectangular Wing With Double-Hinged Nose
"The previous measurements on airfoils with hinged nose disclosed a comparatively large low-pressure peak at the bend of the hinged nose; which favored the separation of flow. It was therefore attempted to reduce these low-pressure peaks by reducing the camber of the forward profile and thereby ensure a longer adherence of the flow and a maximum lift increase. The forces were measured on a rectangular wing with double-hinged nose and end plates, the pressure distributions were measured in the center section of the wing" (p. 1).
Date:
March 1947
Creator:
Lemme, H. A.
Object Type:
Report
System:
The UNT Digital Library