National Advisory Committee for Aeronautics (NACA) - 209 Matching Results

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Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds

Description: "An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale model of the Fairchild Lark missile. The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses" (p. 1).
Date: September 28, 1949
Creator: Martin, Andrew & Hunter, Harlo A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of Two All-Movable Wings Tested in the Presence of a Fuselage at a Mach Number of 1.9

Description: Report presenting testing of half-span models of two wings of different plan form as both all-movable and fixed surfaces in the presence of a half fuselage. All-movable surfaces are being considered for supersonic aircraft as possible angle-of-attack indicators, control surfaces, and all-movable wings. Results regarding the lift characteristics, center of pressure, and drag of the wings are provided.
Date: October 28, 1948
Creator: Conner, D. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of two rectangular-plan-form, all moveable controls in combination with a slender body of revolution at Mach numbers from 3.00 to 6.25

Description: Report presenting the results of force and moment tests at a range of Mach numbers on two rectangular-plan-form, all-movable controls in combination with a slender body of revolution are presented and compared with the predictions of theory. The results showed that lift variations with angle of attack were somewhat nonlinear for both control-body combinations tested.
Date: December 28, 1955
Creator: Wong, Thomas J. & Gloria, Hermilo R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25

Description: Aerodynamic characteristics of rectangular platform, all-movable controls combined with slender body of revolution at Mach 3 to 6.25. The results showed that lift variations with angle of attack were somewhat nonlinear for both control-body combinations tested.
Date: December 28, 1955
Creator: Wong, Thomas J. & Gloria, Hermilo R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Loading Characteristics in Sideslip of a 45 Degree Sweptback Wing With and Without a Fence at High Subsonic Speeds

Description: Report presenting an investigation of the effects of sideslip on the aerodynamic loading characteristics of a 45 degree sweptback wing of aspect ratio 4 for a range of angles of attack, angles of sideslip, and Mach numbers. The load distributions, root bending-moment coefficient, and rolling moment due to sidestep were explored.
Date: January 28, 1955
Creator: Kuhn, Richard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aeronautical interference effects on normal and axial force coefficients of several engine-strut-body configurations at Mach numbers of 1.8 and 2.0

Description: Report presenting an investigation of the aerodynamic interference effects associated with a missile configuration, consisting of a pointed body of revolution with one or two ramjet engines strut-mounted in a vertical plane through the center line of the body, at several engine locations relative to the body and a range of angles of attack. The experimental data indicated increases in slope of the normal force curve with outward movement of the engines. Results regarding the characteristics of … more
Date: April 28, 1952
Creator: Kremzier, Emil J. & Dryer, Murray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aircraft Accidents: Method of Analysis

Description: The revised report includes the chart for the analysis of aircraft accidents, combining consideration of the immediate causes, underlying causes, and results of accidents, as prepared by the special committee, with a number of the definitions clarified. A brief statement of the organization and work of the special committee and of the Committee on Aircraft Accidents; and statistical tables giving a comparison of the types of accidents and causes of accidents in the military services on the one … more
Date: January 28, 1930
Creator: Committee on Aircraft Accidents
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine

Description: An investigation of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel with a full-scale turbojet engine and an 29-inch-diameter tail-pipe burner. Effects of fuel distribution and number and arrangement of stages on performance and operational characteristics of several fuel-cooled flame holders are presented and discussed. Operation with a three-stage flame holder having the large stage upstream was the most efficient. Combustion efficiency was slightly increased at high al… more
Date: April 28, 1950
Creator: Golladay, Richard L. & Bloomer, Harry E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude performance of a full-scale turbojet engine using pentaborane fuels

Description: From Introduction: "The data presented herein include the standard engine performance parameters of net thrust, specific fuel consumption, and engine total-pressure ratio that reflect the performance available from the use of pentaborane as a fuel. The influence of the boric oxide deposits from the high-concentration pentaborane fuels on engine component performance is presented."
Date: February 28, 1957
Creator: Useller, James W.; Kaufman, Warner B. & Jones, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude performance of J71-A-2(600-D1) turbojet engine

Description: From Introduction: "As part of a complete investigation of the J71-A-2(600-D1) turbojet engine conducted in an altitude test chamber at the NACA Lewis laboratory, the steady-state altitude performance, with afterburner inoperative and ejector shroud removed, was obtained and is presented herein. The component performance of the J71-A-2(600-D1) turbojet engine is presented in reference 1. The effects of compressor interstage bleed and adjustable inlet guide vanes on compressor-stall characterist… more
Date: December 28, 1956
Creator: Smith, Ivan D. & Sivo, Joseph N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

Description: "The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel in… more
Date: July 28, 1958
Creator: Groesbeck, Donald E. & Peters, Daniel J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of R-4360-18 Power-Plant Installation for XR60 Airplane, 3, Performance of Induction and Exhaust Systems

Description: From Summary: "A study has been made of the performance of the induction and the exhaust systems on the XR60 power-plant installation as part of an investigation conducted in the Cleveland altitude wind tunnel. Altitude flight conditions from 5000 to 30,000 feet were simulated for a range of engine powers from 750 to 3000 brake horsepower."
Date: March 28, 1947
Creator: Dupree, David T. & Hawkins, W. Kent
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of a Pressure-Jet Power Plant for Helicopter

Description: From Introduction: "In comparison with the shaft-driven rotor, the jet rotor is shown in references 1 and 2 to provide direct reductions in helicopter empty weight and to increase the pay-load capacity by (1) eliminating the gear-reduction train between the rotor shaft and the power plant, (2) eliminating the antitorque tail rotor, and (3) using a power plant of low specific weight."
Date: March 28, 1955
Creator: Krebs, Richard P. & Miller, William S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of life expectancy of airplane wings in normal cruising flight

Description: From Summary: "In order to provide a basis for judging the relative importance of wing failure by fatigue and by single intense gusts, an analysis of wing life for normal cruising flight was made based on data on the frequency of atmospheric gusts. The independent variables considered in the analysis included stress-concentration factor, stress-load relation, wing loading, design and cruising speeds, design gust velocity, and airplane size. Several methods for estimating fatigue life from gust … more
Date: May 28, 1945
Creator: Putnam, Abbott A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of the Full-Floating Journal Bearing

Description: "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 w… more
Date: January 28, 1947
Creator: Shaw, M. C. & Nussdorfer, T. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analytical and Experimental Study of the Effect of Periodic Blade Twist on the Thrust, Torque, and Flapping Motion of an Autogiro Rotor

Description: From Summary: "An analysis is made of the influence on autogiro rotor characteristics of a periodic blade twist that varies with the azimuth position of the rotor blade and the results are compared with experimental data. The analysis expresses the influence of this type of twist upon the thrust, torque, and flapping motion of the rotor. The check against experimental data shows that the periodic twist has a pronounced influence on the flapping motion and that this influence is accurately predi… more
Date: January 28, 1937
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of wing-body theory to drag reduction at low supersonic speeds

Description: Report presenting a method for extending to higher Mach numbers the region of low drag attainable for wing-body combinations by the use of the transonic area rule. To a good approximation, the drag depends only on the longitudinal distributions of area and moments of area about the vertical plane of symmetry parallel to the free-stream direction. The experimental results confirm the theory in that the zero-lift wave drag of a wing-body configuration over a range of low supersonic Mach numbers.
Date: January 28, 1955
Creator: Baldwin, Barrett S., Jr. & Dickey, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Attenuation of Tangential-Pressure Oscillations in a Liquid-Oxygen-n-Heptane Rocket Engine With Longitudinal Fins

Description: Attenuation of tangent-pressure oscillation in liquid-oxygen-heptane rocket engine combustion chamber using longitudinal fin. Results regarding the engine performance with injector A, effect of fins with injector A, and destructiveness of screaming are provided.
Date: June 28, 1956
Creator: Priem, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Attenuation of tangential-pressure oscillations in a liquid-oxygen - n-heptane rocket engine with longitudinal fins

Description: An investigation of the use of fins to prevent high-frequency combustion-pressure oscillations (screaming) in the combustion chamber of a 1000-pound-thrust rocket engine with a chamber pressure of 300 pounds per square inch and using liquid oxygen and n-heptane as propellants. Tangential combustion-pressure oscillations were found to be eliminated with longitudinal fins located in the combustion zone. Results regarding engine performance, effect of fins, and destructiveness of screaming are pro… more
Date: June 28, 1956
Creator: Priem, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Bibliography of NACA Reports on Control of Turbojet Engines

Description: Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.
Date: June 28, 1956
Creator: Sanders, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages… more
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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