National Advisory Committee for Aeronautics (NACA) - 2,223 Matching Results

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Wind-tunnel investigation of the static longitudinal stability and trim characteristics of a sweptback-wing jet-transport model equipped with an external-flow jet augmented flap

Description: Report presenting a wind-tunnel investigation to determine the static longitudinal stability and trim characteristics of a sweptback-wing jet-transport model equipped with an external-flow jet-augmented flap. Tests were also conducted to determine the effects of wing position, vertical position of the horizontal tail, and size of the horizontal tail.
Date: January 1958
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability characteristics of a complete-model swept-wing configuration at high subsonic speeds

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Results regarding the methods of analysis and vertical-tail contributions are provided.
Date: November 1956
Creator: Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel studies of the performance of multirotor configurations

Description: Report presenting the power requirements measured in static thrust and in level forward flight for two helicopter rotor configurations. One is a coaxial rotor arrangement with the rotors spaced approximately 19 percent of the rotor radius; the other is a tandem configuration in which the rotor-shaft spacing is 3 percent greater than the rotor diameter and in which the rotors lie in the same plane.
Date: August 1954
Creator: Dingeldein, Richard C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Technique for Simultaneous Simulation of External Flow Field About Nacelle Inlet and Exit Airstreams at Supersonic Speeds

Description: Report presenting an investigation of several ways of simultaneously simulating the external pressure field generated by an engine exhaust jet and an air inlet. The results indicated that the pressure field in the vicinity of the exit station and external to a real exhaust jet could be adequately simulated while keeping the inlet at critical or supercritical mass flow. Results for a target probe, a perforated probe, and the pressure and airflow required in the probes are provided.
Date: January 1957
Creator: Englert, Gerald W. & Luidens, Roger W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests at low speed of swept and yawed wings having various plan forms

Description: Results are presented of wind-tunnel tests made at low speed of various small-scale models of sweptback, sweptforward, and yawed wings. The tests covered changes in aspect ratio, taper ratio, and tip shape. Some data were obtained with high-lift devices on sweptback wings and with ailerons on sweptforward wings. The data have been briefly analyzed and some comparisons have been made with the available theory.
Date: December 1951
Creator: Purser, Paul E. & Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel tests of a full-scale helicopter rotor with symmetrical and with cambered blade sections at advance ratios from 0.3 to 0.4

Description: Report presenting wind tunnel testing of a 44-foot-diameter, three-bladed helicopter rotor to investigate the performance gains made available by delaying retreating blade stall by the use of blade sections with increased maximum lift. Comparison of the stall boundaries showed that blades with cambered sections were superior to blades with symmetrical sections due to the increase in lifting capacity and forward speed capacity. Results regarding the determination of retreating blade stall, stall… more
Date: September 1958
Creator: McCloud, John L., III & McCullough, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-Body Combinations With Certain Geometric Restraints Having Low Zero-Lift Wave Drag at Low Supersonic Mach Numbers

Description: "Several variational problems involving optimum wing and body combinations having minimum wave drags for different kinds of geometrical restraints are analyzed. Particular attention is paid to the effect on the wave drag of shortening the fuselage and, for slender axially symmetric bodies, the effect of fixing the fuselage diameter at several points or even of fixing whole portions of its shape" (p. 1).
Date: February 1956
Creator: Lomax, Harvard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-body interference at supersonic speeds with an application to combinations with rectangular wings

Description: Report presenting the development of an exact theoretical method that permits the determination of the pressure field of a wing-body combination with a circular body and a wing with supersonic leading and trailing edges. Detailed calculations were performed for wing-body combinations composed of rectangular wings mounted at incidence on bodies at zero angle of attack for effective chord-radius ratios of 4 or less.
Date: April 1952
Creator: Nielsen, Jack N. & Pitts, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wing-Tunnel Investigation of Effects of Various Aerodynamic Balance Shapes and Sweepback on Control-Surface Characteristics of Semispan Tail Surfaces With NACA 0009, 0015, 66-009, 66(215)-014, and Circular-Arc Airfoil Sections

Description: Note presenting a summary of force data on unswept and sweptback airplane control surfaces. Lift and hinge-moment characteristics were determined for four unswept, semispan control surfaces, and lift, drag, hinge moment, and pitching moment were determined for two semispan, sweptback control surfaces. Measured values of the parameters are compared with those obtained from section data by application of lifting-surface and lifting-line theory.
Date: October 1951
Creator: Harper, John J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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X-Ray Diffraction by Bent Crystal Lamellae

Description: Note presenting an overview of bent crystal lamellae, which may consist of individual blocks, spaced somewhat irregularly and with a mutual angular disorientation. In this case, the x-ray intensities of the individual blocks will simply be added. A study was done to determine if there was any difference between diffraction by a bent lamella and by an array of irregularly spaced blocks arranged in a circle.
Date: September 1951
Creator: Ekstein, Hans
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

X-Ray Diffraction Study of the Internal Structure of Supercooled Water

Description: From Summary: "A Bragg X-ray spectrometer equipped with a volume-sensitive Geiger counter and Soller slits and employing filtered molybdenum Ka radiation was used to obtain a set of diffracted intensity curves as a Punction of angle for supercooled water. Diffracted intensity curves in the temperature region of 21 to -16 C were obtained. The minimum between the two main diffraction peaks deepened continuously with lowering temperature, indicating a gradual change in the internal structure of th… more
Date: October 1951
Creator: Dorsch, Robert G. & Boyd, Bemrose
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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X-Ray Instrumentation for Density Measurements in a Supersonic Flow Field

Description: Report describing an instrument based on the principle that an x-ray beam is essentially undeviated while traversing a short path in air. It was used to measure the product of air density and the path length in the 10- by 14-inch supersonic wind tunnel. The measurements obtained were accomplished by comparing the intensity of two beams from the same X-ray source.
Date: December 1952
Creator: Dimeff, John; Hallett, Ralph K., Jr. & Hansen, C. Frederick
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The zero-lift drag of a 60 degree delta-wing-body combination (AGARD model 2) obtained from free-flight tests between Mach numbers of 0.8 and 1.7

Description: From Summary: "The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4 x 10(exp 6) and 12 x 10(exp 6), respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good."
Date: April 1954
Creator: Piland, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The zero-lift drag of a slender body of revolution (NACA RM-10 research model) as determined from tests in several wind tunnels and in flight at supersonic speeds

Description: Presents zero-lift drag data of an NACA RM-10 slender body of revolution with and without stabilizing fins attached. The results from several wind tunnels and in flight are compared. The results cover a Reynolds number range from about 1 time 10 to the 6th power to 40 times 10 to the 6th power for the flight models. The Mach numbers covered include 1.5 to 2.4 in the wind tunnels and 0.85 to 2.5 in flight.
Date: April 1953
Creator: Evans, Albert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Zero-Lift Wave Drag of a Particular Family of Unswept, Tapered Wings With Linearly Varying Thickness Ratio

Description: Report presenting the zero-lift wave drag of a particular family of unswept, tapered wings with linearly varying thickness ratio and symmetrical parabolic-arc sections. It is found that the variable-thickness-ratio wings can be used to advantage with no serious structural penalties if the wings have the same given root thickness ratio or internal volume. Results regarding the given frontal area and given volume are provided.
Date: May 1955
Creator: Henderson, Arthur, Jr. & Goodwin, Julia M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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