National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

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Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-Cylinder-Flare Configuration in Free Flight at Mach Numbers Up to 4.7

Description: Report presenting measurements of aerodynamic heat transfer at a number of stations along a cone-cylinder-flare model with 15 degree total-angle conical nose and a 10 degree half-angle flare skirt. Results regarding temperature measurements and heating rates, local flow parameters, heat transfer with theoretical recovery factors, experimental recovery factors, prediction of skin temperatures, and transition are provided.
Date: January 22, 1958
Creator: Rumsey, Charles B. & Lee, Dorothy B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Simulator Investigation of Factors Affecting the Design and Utilization of a Stick Pusher for the Prevention of Airplane Pitch-Up

Description: Memorandum presenting the results of a simulator stud of the factors affecting the design of a device, a stick pusher, for preventing a representative supersonic airplane from entering the pitch-up region. The effects of varying the stick-pusher-activation boundaries, sensing parameters, and magnitude of stick-pusher force on the controllability of the airplane pitch-up were investigated.
Date: January 22, 1958
Creator: Holleman, Euclid C. & Boslaugh, David L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22 : longitudinal characteristics of a triangular wing and canard

Description: Report presenting the results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers. Data are presented for a variety of angles of attack and canard angles.
Date: January 22, 1958
Creator: Boyd, John W. & Peterson, Victor L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Leading-Edge Slat and Trailing-Edge Split Flap on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a Nearly Triangular Wing of Aspect Ratio 2.9 at Mach Numbers From 0.60 to 0.92

Description: Report presenting an investigation to determine the effectiveness of a leading-edge slat and a trailing-edge split flap in improving the high subsonic speed aerodynamic characteristics of a model of a wing-fuselage combination with a nearly triangular wing. Results regarding the effects of Reynolds number, effects of slats, and effects of flaps are provided.
Date: January 24, 1958
Creator: Demele, Fred A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-flight roll performance of a steady-flow jet-spoiler control on an 80 degree delta-wing missile between Mach numbers of 0.6 and 1.8

Description: Report presenting a free-flight investigation of the zero-lift control effectiveness of a steady-flow jet-spoiler roll control on a cruciform 80 degree delta-wing missile over a range of Mach numbers. Measurements were made of the rolling-moment, damping-in-roll derivative, drag, and pressures at the inlet and on the wing near the jet exit. Results indicated that the wing and jet combination magnified the thrust force of the isolated jet alone by factors of 11 at subsonic speeds to 3 at superso… more
Date: January 24, 1958
Creator: Schult, Eugene D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane

Description: Memorandum presenting a transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane in the transonic blowdown tunnel. The models were dynamically and elastically scaled by criteria which provide a flutter safety margin. Results regarding some general comments, simulated airplane tests, effects of pitch stiffness with rearward pitch axis, and effect of pitch-axis location are provided.
Date: January 24, 1958
Creator: Sellers, Thomas B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane

Description: Report presenting an investigation of the transonic flutter characteristics of models of an all-movable horizontal tail of a fighter airplane. Results regarding simulated airplane tests, the effects of pitch stiffness with rearward pitch axis, and the effect of pitch-axis location are provided.
Date: January 24, 1958
Creator: Sellers, Thomas B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Use of Leading-Edge and Trailing-Edge Area-Suction Flaps on a 13-Percent-Thick Straight Wing and Fuselage Model

Description: Report presenting a wind-tunnel investigation to determine the effectiveness of area suction in increasing the lift of a moderately thick straight wing encountering trailing-edge air flow separation. Results regarding a model with undeflected leading-edge flap and tip tanks on and a model with the tip tanks removed are provided.
Date: January 24, 1958
Creator: Holzhauser, Curt A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 by 10 to the 6th Power

Description: Report discussing heat-transfer and pressure measurements obtained from flight testing of a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. The heat-transfer coefficients were compared to theoretical results and a discrepancy was found during the accelerating portions of flight. Drag coefficients were obtained for a range of Mach numbers.
Date: January 29, 1958
Creator: Graham, John B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model on the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 X 10(Exp 6) : Coord. No. AF-AM-70

Description: Report presenting heat-transfer and pressure measurements obtained from flight tests of a model of the Titan intercontinental ballistic missile. Turbulent flow was observed over the model throughout the flight with the exception of one station on the nose. Results regarding pressure measurements, heat transfer, and drag measurements are required.
Date: January 29, 1958
Creator: Graham, John B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Degree Swept- Wing-Fuselage Configuration at a Mach Number of 1.61

Description: Forces and moments of store-pylon combination mounting on swept wing-fuselage configuration in supersonic pressure tunnel. The results of the investigation indicate that the most important source of store-pylon side forces is the pylon itself.
Date: January 30, 1958
Creator: Morris, Odell A.; Carlson, Harry W. & Geier, Douglas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability Investigation of a Vertical-Take-Off-and-Landing Airplane Configuration With Simulated Jet Intake and Exhaust at Mach Numbers of 1.61 and 2.01

Description: Report presenting an investigation of a semispan model of a possible vertical-take-off-and-landing jet bomber configuration at a range of Mach numbers. The primary objective was to determine to the effects of jet interference, horizontal-tail location, and canard controls on the longitudinal stability characteristics of the model.
Date: January 30, 1958
Creator: Lord, Douglas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Description: Report presenting the performance of a two-dimensional side inlet with a technique of varying compression-surface angle while retaining a fixed-geometry diffuser at several Mach numbers and zero angle of attack. A 12 degree compression ramp was faired into the diffuser contour in this conventional manner. Results regarding the inlet flow field, application to reduced engine speeds, and a inlet performance with a sudden expansion in the diffuser are provided.
Date: January 30, 1958
Creator: Allen, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds

Description: The performance of NACA 65-series compressor blade section in cascade has been investigated systematically in a low-speed cascade tunnel. Porous test-section side walls and for high-pressure-rise conditions, porous flexible end walls were employed to establish conditions closely simulating two-dimensional flow. Blade sections of design lift coefficients from 0 to 2.7 were tested over the usable angle-of-attack range for various combinations of inlet-flow angle. A sufficient number of combinatio… more
Date: January 31, 1958
Creator: Emery, James C.; Herrig, L. Joseph; Erwin, John R. & Felix, A. Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Accelerations in Transport-Airplane Crashes

Description: From Introduction: "A study of crash-impact survival in light airplanes is reported in references 1 and 2. A similar study for fighter airplanes is reported in reference 3. This report discusses crash-impact survival in transport airplanes."
Date: February 1958
Creator: Preston, G. Merritt & Pesman, Gerard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil

Description: From Summary: "The effects of ice formations on the section lift, drag, and pitching-moment coefficients of an unswept NACA 65A004 airfoil section of 6-foot chord were studied.. The magnitude of the aerodynamic penalties was primarily a function of the shape and size of the ice formation near the leading edge of the airfoil. The exact size and shape of the ice formations were determined photographically and found to be complex functions of the operating and icing conditions."
Date: February 1958
Creator: Gray, Vernon H. & von Glahn, Uwe H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of the turbulent boundary-layer characteristics on a flat plate with distributed light-gas injection

Description: From Introduction: "The present paper is concerned with a transpiration cooling system in which the coolant passes through the surface it is protecting before entering the surrounding boundary layer. Analyses and experiments have been performed to determine the effect of distributed air transportation through flat surfaces over which air flows in turbulent boundary layer (refs. 2, 3, and 4)."
Date: February 1958
Creator: Rubesin, Morris W. & Pappas, Constantine C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-layer transition on an open-nose cone at Mach 3.1

Description: Report presenting comparison of transition locations for an open-nose cone, a conventional sharp cone, and a hollow cylinder showed that transition locations on the open-nose cone and hollow cylinder were identical but differed from the sharp cone. Bluntness effects on the open-nose cone were quite similar to those observed on the hollow cylinder.
Date: February 1958
Creator: Brinich, Paul F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Charts Relating the Compressive and Shear Buckling Stresses of Longitudinally Supported Plates to the Effective Deflectional Stiffness

Description: "A stability analysis is made of long flat rectangular plates subjected to both shear and compressive loads. The edges of the plates are taken to be simply supported and the plates are supported along one or two intermediate longitudinal lines by lines of deflectional springs (elastic line supports). The results of the analysis are presented in the form of charts that are useful in the determination of the buckling load of plates stiffened by stringers or webs" (p. 1).
Date: February 1958
Creator: Johnson, Aldie E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of hydrodynamic-impact acceleration and response for systems with single and with multiple elastic modes

Description: Report presenting hydrodynamic impact testing made with a multimode elastic model consisting of a rigid prismatic float and a flexible wing and a comparison with similar experimental results for a single-mode system and with theoretical solutions. Testing was conducted in smooth water at two fixed trims and two flight-path angles over a range of velocities. Results regarding accelerations, time histories, oscillatory accelerations, elastic-body acceleration data, and rigid-body acceleration dat… more
Date: February 1958
Creator: Miller, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compilation of information on the transonic attachment of flows at the leading edges of airfoils

Description: Schlieren photographs have been compiled of the two-dimensional flow at transonic speeds past 37 airfoils. These airfoils have variously shaped profiles, and some are related in thickness and camber. The data for these airfoils were analyzed to provide basic information on the flow changes involved and to determine factors affecting transonic-flow attachment, which is a transition from separated to unseparated flow at the leading edges of two-dimensional airfoils at fixed angles as the subsonic… more
Date: February 1958
Creator: Lindsey, Walter F. & Landrum, Emma Jean
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Correlations Among Ice Measurements, Impingement Rates Icing Conditions, and Drag Coefficients for Unswept NACA 65A004 Airfoil

Description: "An empirical relation has been obtained by which the change in drag coefficient caused by ice formations on an unswept NACA 65A004 airfoil section can be determined from the following icing and operating conditions: icing time, airspeed, air total temperature, liquid-water content, cloud droplet impingement efficiencies, airfoil chord length, and angles of attack. The correlation was obtained by use of measured ice heights and ice angles. These measurements were obtained from a variety of ice … more
Date: February 1958
Creator: Gray, Vernon H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Creep of Aluminum-Copper Alloys During Age Hardening

Description: Note presenting a study of the interrelation of aging during creep and of creep during aging in polycrystalline aluminum alloys containing 1 to 4 percent copper. Experimental procedures included interrupted creep tests, tensile tests of crept specimens, quantitative metallographic determination of the percent precipitation during creep, hardness measurements on unstressed and stressed aged alloys, X-ray studies of deformation in the crystalline lattice, and microscopic examination of the surfac… more
Date: February 1958
Creator: Underwood, E. E.; Marsh, L. L. & Manning, G. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Minimization for Wings in Supersonic Flow, With Various Constraints

Description: Report presenting a study of the minimization of inviscid fluid drag for thin aerodynamic shapes subject to imposed constraints on lift, pitching moment, base area, or volume. The problem is transformed to one or determining a two-dimensional potential flow satisfying either Laplace's or Poisson's equations with boundary values fixed by the imposed conditions.
Date: February 1958
Creator: Heaslet, Max A. & Fuller, Franklyn B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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