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Flight Investigation to Determine the Aerodynamic Characteristics of Rocket-Powered Models Representative of a Fighter-Type Airplane Configuration Incorporating an Inverse-Taper Wing and a Vee Tail

Description: From Summary: "Two rocket-powered models representative of a fighter-type airplane were investigated in flight at Mach numbers up to 1.01 and 1.07 by the Langley Pilotless Aircraft Research Division at its testing station at Wallops Island, Va. These models incorporated an inverse-taper wing and a vee tail and were flown with controls undeflected and wing and stabilizer set at 0 deg incidence. Values of lateral acceleration, normal acceleration velocity, and drag were obtained by use of telemet… more
Date: November 2, 1948
Creator: Alexander, Sidney R.
Partner: UNT Libraries Government Documents Department
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The Effects of Changes in Aspect Ratio and Tail Height on the Longitudinal Stability Characteristics at High Subsonic Speeds of a Model With a Wing Having 32.6 Degree Sweepback

Description: Report discussing an investigation to determine the effects of changes in aspect ratio and tail height on the longitudinal stability characteristics of a model with a 32.6-degree sweptback wing. The effects of a leading-edge discontinuity were also examined.
Date: February 2, 1954
Creator: Alford, William J., Jr. & Pasteur, Thomas B., Jr.
Partner: UNT Libraries Government Documents Department
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Investigation of a trailing-edge paddle-control surface on a triangular wing of aspect ratio 2 at subsonic and supersonic speeds

Description: Report presenting an experimental investigation of external airfoils, known as paddle-control surfaces, as the longitudinal control device on a triangular wing of aspect ratio 2. The lift, drag, pitching moment, and hinge moment were obtained for a variety of Mach numbers.
Date: February 2, 1954
Creator: Ball, Louis H.
Partner: UNT Libraries Government Documents Department
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Survey of two-dimensional data on pitching-moment changes near maximum lift caused by deflection of high-lift devices

Description: Report presenting a survey of two-dimensional data on trim changes near maximum lift resulting from deflection of various types of leading-edge and trialing-edge high lift devices. Results regarding pitching-moment coefficients, pitching-moment increments, and maximum lift coefficients are provided.
Date: December 2, 1949
Creator: Bidwell, Jerold M. & Cahill, Jones F.
Partner: UNT Libraries Government Documents Department
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A transonic wind-tunnel investigation of the effects of nacelle shape and position on the aerodynamic characteristics of two 47 degree sweptback wing-body configurations

Description: Report presenting an investigation in the 8-foot transonic tunnel to determine the effect of nacelle shape and position on the aerodynamic characteristics of two wing-body configurations at a range of Mach numbers. Some of the nacelles investigated included underslung and pylon-suspended nacelles located at the 40 percent-semispan station, submerged nacelles, and wing-tip nacelles. Results regarding the drag characteristics, mass-flow characteristics, schileren photographs, lift characteristics… more
Date: September 2, 1952
Creator: Bielat, Ralph P. & Harrison, Daniel E.
Partner: UNT Libraries Government Documents Department
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Experimental results of an investigation of two methods of inflight thrust measurement applicable to afterburning turbojet engines with ejectors

Description: Report presenting an investigation in an altitude test chamber using a turbojet engine equipped with an afterburner and ejector to compare directly two techniques of determining thrust that are both applicable to flight installations. One method uses a swinging uncooled rake at the ejector outlet while the other requires extensive instrumentation to measure the momentum forces of systems and the force on the internal surface of the ejector nozzle. Results regarding the swinging-rake technique a… more
Date: May 2, 1958
Creator: Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Jet Effects on a Flat Surface Downstream of the Exit of a Simulated Turbojet Nacelle at a Free-Stream Mach Number of 1.39

Description: Report presenting an investigation utilizing a blowdown-type tunnel to determine the effects of a propulsive jet on a zero angle-of-attack wing surface located in the vicinity of both a choked convergent nozzle and a convergent-divergent nozzle. Static-pressure surveys were made on a flat surface located in the vicinity of the propulsive jet. Results regaridng the jet-off and jet-on pressure coefficients, shock waves, and incremental normal force are provided.
Date: April 2, 1956
Creator: Bressette, Walter E. & Leiss, Abraham
Partner: UNT Libraries Government Documents Department
open access

Cloud-droplet ingestion in engine inlets with inlet velocity ratios of 1.0 and 0.7

Description: From Summary: "The paths of cloud droplets into two engine inlets have been calculated for a wide range of meteorological and flight conditions. The amount of water in droplet form ingested by the inlets and the amount and distribution of water impinging on the inlet walls are obtained from these droplet-trajectory calculations. In both types of inlet, a prolate ellipsoid of revolution represents either part or all of the forebody at the center of an annular inlet to an engine. The configuratio… more
Date: November 2, 1955
Creator: Brun, Rinaldo J.
Partner: UNT Libraries Government Documents Department
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The Effects at Subsonic Speeds of Wing Fences and a Tail on the Longitudinal Characteristics of a 63 Degree Swept-Wing Fuselage Combination

Description: Report presenting wind-tunnel testing to evaluate the effects of wing fences and a tail on the longitudinal characteristics of a highly swept wing in combination with a fuselage. The model, which had a cambered and twisted wing with a leading-edge sweepback of 63 degrees and an aspect ratio of 3.5, was tested with fences of various shapes and swept and unswept horizontal tails. Results regarding exploratory tests, final-configuration tests, static longitudinal stability factors, and maximum lif… more
Date: July 2, 1957
Creator: Buell, Donald A. & Kolbe, Carl D.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Description: Report presenting flight testing of a rocket-propelled model of a typical multiengine airplane configuration to obtain data on drag, stability, and nacelle performance. Data were obtained at a variety of Mach numbers, lift coefficients, and subsonic and supersonic speeds. Results regarding airplane performance, nacelle performance, longitudinal characteristics, and lateral characteristics are provided.
Date: September 2, 1955
Creator: Chapman, Rowe, Jr.
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.70 to 1.37 of Rocket-Propelled Models Having a Modified Triangular Wing

Description: "A modified triangular wing of aspect ratio 2.53 having an airfoil section 3.7 percent thick at the root and 5.98 percent thick at the tip was designed in an attempt to improve the lift and drag characteristics of triangular wings. Free-flight drag and stability tests were made using rocket-propelled models equipped with the modified wing. The Mach number range of the test was from 0.70 to 1.37" (p. 1).
Date: May 2, 1952
Creator: Chapman, Rowe, Jr. & Morrow, John D.
Partner: UNT Libraries Government Documents Department
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A Study of Visual Interception Attacks on a Nonmaneuvering Airplane Target

Description: Report presenting a study and evaluation of interception attacks made by an experienced pilot flying a Grumman F9F-3 airplane on a nonmaneuvering target. The runs were made under visual conditions at subsonic speeds and an altitude of 30,000 feet. Results regarding interceptor control characteristics, tracking characteristics, effect of interceptor turning capabilities, data significant to design of interceptor control systems, and evaluations applied to the automatic control apparatus.
Date: July 2, 1953
Creator: Cheatham, Donald C.; Mathews, Charles W. & Harper, John A.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Static Aerodynamic and Dynamic Damping-in-Roll Characteristics of an 8-Cm Aircraft Rocket With Solid and Slotted Fins

Description: Memorandum presenting an investigation of the static aerodynamic and dynamic damping-in-roll characteristics of an aircraft rocket with cruciform fins of trapezoidal plan form as determined experimentally at a range of Mach numbers. The fins had tow holes cut through each fin panel, and the effects of the holes or slots were investigated by testing with both solid and slotted fins.
Date: June 2, 1952
Creator: Chubb, Robert S.
Partner: UNT Libraries Government Documents Department
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Effect of Inlet Air Distortion on the Steady-State and Surge Characteristics of an Axial-Flow Turbojet Compressor

Description: "An investigation was conducted in an altitude test chamber to determine the effects of inlet airflow distortion on the compressor steady-state and surge characteristics of a high-pressure ratio, axial-flow turbojet engine. Circumferential-type inlet flow distortions were investigated, which covered a range of distortion sector angles from 20 deg to 168 deg and distortion levels up to 22 percent. The presence of inlet airflow distortions at the compressor face resulted in a substantial increase… more
Date: January 2, 1948
Creator: Ciepluch, Carl C.
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Lateral Control Characteristics of an Airplane Equipped With a Combination Aileron-Spoiler Control System

Description: Report presenting flight tests conducted to measure the lateral-control characteristics of an airplane, equipped with a lateral-control system, in which as the flaps are lowered the ailerons droop and a gradual transition of lateral control from ailerons to spoilers takes place. The variation of maximum rolling velocity with lateral stick movement as obtained in abrupt rudder-locked rolls was satisfactorily smooth except when control was by spoiler alone.
Date: September 2, 1942
Creator: Clousing, Lawrence A. & McAvoy, William H.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of air-cooled turbine blades in turbojet engine 11: internal-strut-supported rotor blade

Description: Report presenting an investigation of an air-cooled internal-strut-supported blade in a modified production turbojet engine to determine the cooling effectiveness of this type of blade and the cooling-air pressure loss through the blade under engine operating conditions. Experimental results are presented and compared with the results of an analytical investigation.
Date: June 2, 1952
Creator: Cochran, Reeves P.; Stepka, Francis S. & Krasner, Morton H.
Partner: UNT Libraries Government Documents Department
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The Use of Area Suction for the Purpose of Improving Trailing-Edge Flap Effectiveness on a 35 Degree Sweptback Wing

Description: "An investigation was conducted to determine the effectiveness of suction applied through a porous area at the leading edge of the flap, on a 35 degree sweptback wing. Several chordwise extents and positions of area suction were tested for the suction flap deflected 55 degrees and 70 degrees. The results indicated that large increases in flap lift increment can be made by applying suction with very small flow quantities to an area near the leading edge of a flap" (p. 1).
Date: July 2, 1953
Creator: Cook, Woodrow L.; Holzhauser, Curt A. & Kelly, Mark W.
Partner: UNT Libraries Government Documents Department
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Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap

Description: Report presenting an investigation at supersonic speeds of some of the factors affecting the flow over a rectangular wing with a symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. The main purpose is to obtain more information on which to base the design of supersonic controls. Results regarding the effect of Mach number, effect of wing thickness, effect of fixing transition, effect of sealing the hinge gap, effect of model surface condition and asymmetry, and shock bou… more
Date: January 2, 1951
Creator: Czarnecki, K. R. & Mueller, James N.
Partner: UNT Libraries Government Documents Department
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An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane

Description: Report presenting wind-tunnel testing of submerged air inlets on the fuselage of a scale model of a typical fighter-type airplane. The results are presented for ramp plan forms with parallel and with diverging walls and show the effect of the duct-entrance location, internal ducting efficiency, and deflectors.
Date: June 2, 1948
Creator: Delany, Noel K.
Partner: UNT Libraries Government Documents Department
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Correlation of forced-convection heat-transfer data for air flowing in smooth platinum tube with long-approach entrance at high surface and inlet-air temperatures

Description: A heat-transfer investigation was conducted with air in an electrically heated platinum tube with long-approach entrance, inside diameter of 0.525 inch, and effective heat-transfer length of 24 inches over ranges of Reynolds number up to 320,000, average inside-tube-wall temperature up to 3053 degrees R, and inlet-air temperature up to 1165 degrees R. Correlation of data by the conventional Nusselt relation resulted in separation of data with tube-wall temperature. Good correlation was obtained… more
Date: November 2, 1950
Creator: Desmon, Leland G. & Sams, Eldon W.
Partner: UNT Libraries Government Documents Department
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The Effect of Moment-of-Area-Rule Modifications on the Zero-Lift Drag of Three Wing-Body Combinations

Description: Memorandum presenting an experimental investigation to determine the effect on drag of applying the moment-of-area-rule modifications to wing-body combinations with various wing plan forms. The effect of mounting air-to-air type missiles on the wing-mounted bodies of revolution which are part of the moment-of-area-rule modification was also investigated.
Date: May 2, 1958
Creator: Dickey, Robert R.
Partner: UNT Libraries Government Documents Department
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An Approximate Method for Estimating the Incompressible Laminar Boundary-Layer Characteristics on a Flat Plate in Slipping Flow

Description: Memorandum presenting an approximate method for the estimation of the properties of the incompressible laminar boundary layer on a flat plate in the slip-flow region using Karman's momentum method. At equivalent stations, the total thickness and the skin friction of a slipping boundary layer are less than that of the normal boundary layer at the same Reynolds number.
Date: May 2, 1949
Creator: Donaldson, Coleman duP.
Partner: UNT Libraries Government Documents Department
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Flame velocities of propane- and ethylene-oxygen-nitrogen mixtures

Description: Report presenting the laminar flame velocities of propane and ethylene with various oxygen-nitrogen mixtures as determined from schileren photographs of Bunsen-type flames. Flame velocity was determined as a function of equivalence ratio for each oxygen-nitrogen mixture at two initial temperatures.
Date: January 2, 1953
Creator: Dugger, Gordon L. & Graab, Dorothy D.
Partner: UNT Libraries Government Documents Department
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