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Investigation at low speeds of deflectors and spoilers as gust alleviators on a model of the Bell X-5 airplane with 35 degree swept wings and on a high-aspect-ratio 35 degree swept-wing-fuselage model

Description: Results of an investigation at low speeds to determine the gust-alleviation capabilities (reduction in lift-curve slope) of spoilers and deflectors on a 35 degree swept-wing model of high aspect ratio and on a 1/4-scale model of the X-5 airplane with 35 degree swept wings indicate that deflector and spoiler-deflector types of controls can be designed to provide considerable gust alleviation for a swept-wing airplane while still maintaining stability and control.
Date: June 1957
Creator: Croom, Delwin R. & Huffman, Jarrett K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings

Description: Report presenting a wind-tunnel investigation conducted in rolling flow to determine the effects of aspect ratio and sweep on the rolling stability derivatives for a series of untapered wings. The results indicated that when the aspect ratio is held constant, an increase in sweepback angle causes a significant reduction in the damping in roll at low lift coefficients for only the higher aspect ratios tested.
Date: March 1949
Creator: Goodman, Alex & Fisher, Lewis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at low speeds of the effect of aspect ratio and sweep on rolling stability derivatives of untapered wings

Description: A low-scale wind-tunnel investigation was conducted in rolling flow to determine the effects of aspect ratio and sweep (when varied independently) on the rolling stability derivatives for a series of untapered wings. The rolling-flow equipment of the Langley stability tunnel was used for the tests. The data of the investigation have been used to develop a method of accounting for the effects of the drag on the yawing moment due to rolling throughout the lift range.
Date: January 19, 1949
Creator: Goodman, Alex & Fisher, Lewis R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Low Speeds of the Effect of Aspect Ratio and Sweep on Static and Yawing Stability Derivatives of Untapered Wings

Description: Report presenting a low-scale wind-tunnel investigation in both straight and yawing flow to determine the effects of aspect ratio and sweep on the static and yawing stability derivatives for a series of untapered wings. The effects of sweep on the static stability characteristics, including lift-curve slope, drag, and effective-dihedral parameter, generally became smaller as the aspect ratio decreased.
Date: August 1948
Creator: Goodman, Alex & Brewer, Jack D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap

Description: Report presenting an investigation of the pressure distribution over a rectangular wing with a 9-percent-thick symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. Results are given for pressure distributions, Schileren and liquid-film studies, and wing section characteristics are provided.
Date: January 25, 1950
Creator: Czarnecki, K. R. & Mueller, James N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach Number 1.88 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control

Description: Experimental investigation was conducted at Mach number 1.88 to determine performance characteristics of half a 50 degree-conical-spike inlet mounted on a flat plate. Initial boundary layer was removed up-stream of inlet by a ram-type scoop of variable height. Initial boundary-layer thickness was also varied. With complete removal of initial boundary layer, total-pressure recovery of approximately 70 percent. Several alternative boundary-layer-removal systems were investigated which decreased tā€¦ more
Date: September 19, 1951
Creator: Goelzer, H. Fred & Cortright, Edgar M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach number 1.91 of side and base pressure distributions over conical boattails without and with jet flow issuing from base

Description: Experimental side and blade pressure distributions over a series of conical boattails without and with jet flow from the base are presented at a Mach number of 1.91. For the case of no jet flow the methods of characteristics and linearized theory are shown to overpredict the side pressure drag. A semi-empirical theory is presented to predict the effect of boattail angle on base pressure. With the boattail extending to a sharp edge at the nozzle exit, the over-pressure jet is shown to decrease tā€¦ more
Date: September 12, 1951
Creator: Cortright, Edgar M., Jr. & Schroeder, Albert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles

Description: Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date: February 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach number 1.91 of spreading characteristics of jet expanding from choked nozzles

Description: It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are considerably smaller than the temperature profiles of jets expanding into quiescent air. The effect on the wake of varying afterbody geometry is shown to be small. The gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles in the base of a body of revolution with various boattail configurations at a Mach number of 1.91 are presented.
Date: January 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation at Mach Number 2.40 of Flap-Type Controls Equipped With Overhang Nose Balances

Description: Report presenting some of the factors affecting the two-dimensional characteristics of flap-type controls equipped with overhang nose balances at a Mach number of 2.40. The effects of changing nose-balance overhang, altering the shape of the nose balance, beveling the afterbody of the basic wing forward of the flap nose, varying wing-flap gap size, fixing transition, and varying the flap trailing-edge thickness are presented.
Date: November 17, 1953
Creator: Mueller, James N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach Number 2.93 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control

Description: Report presenting an investigation to determine the performance characteristics of a side inlet with boundary-layer control operating in the presence of laminar and turbulent initial boundary layers at a free-stream Mach number of 2.93. Results regarding mass-flow and total-pressure referencing, visual-flow observations, inlet performance, and boundary-layer-scoop performance are provided.
Date: September 10, 1952
Creator: Piercy, Thomas G. & Johnson, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach numbers 1.5 and 1.7 of twin-duct side air-intake system with 9 degree compression ramp including modifications to boundary-layer-removal wedges and effects of a bypass system

Description: An investigation of the performance of a twin-duct air-intake system with a 9 degree compression-ramp inlet mounted on a supersonic airplane in the 8- by 6-foot supersonic wind tunnel at a range of Mach numbers, angles of attack, yaw, and mass-flow ratios. The effect on performance of a series of boundary-layer-removal wedges and a main-duct airflow bypass system were also investigated.
Date: October 12, 1953
Creator: Obery, Leonard J. & Stitt, Leonard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach numbers 1.5 and 1.7 of twin-duct side intake system with two-dimensional 6 degree compression ramps mounted on a supersonic airplane

Description: Report presenting an experimental investigation in the 8- by 6-foot supersonic wind tunnel to determine the performance characteristics of a twin-duct side intake system joining into a common duct and utilizing two-dimensional 6 degree compression ramps mounted on a supersonic airplane at Mach numbers 1.5 and 1.7.
Date: October 12, 1953
Creator: Davids, Joseph & Wise, George A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation at Mach Numbers 2.98 and 2.18 of Axially Symmetric Free-Jet Diffusion with a Ram-Jet Engine

Description: "An investigation was conducted to determine the effectiveness of a free-jet diffuser in reducing the over-all pressure ratios required to operate a free jet with a large air-breathing engine as a test vehicle. Efficient operation of the free jet was determined with and without the considerations required for producing suitable engine-inlet flow conditions. A minimum operating pressure ration of 5.5 was attained with a ratio of nozzle-exit to engine-inlet area of 1.85" (p. 1).
Date: February 13, 1952
Creator: Hunczak, Henry R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation at Mach numbers of 1.40 and 1.59 of the effects of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration

Description: An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel at Mach numbers 1.40 and 1.59 to determine the effect of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The ailerons were 20-percent chord and were located on the outboard 50 percent of the wing semispans. The various aileronsā€¦ more
Date: January 15, 1951
Creator: Spearman, M. Leroy & Webster, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach numbers of 1.41, 1.61, and 1.82 of two variable-geometry inlets having two-dimensional compression surfaces

Description: Report presenting one-tenth-scale models of two inlet configurations of fighter-type aircraft have been tested in the 4- by 4-foot supersonic pressure tunnel. The pressure-recovery and force characteristics of the inlets were determined as a function of mass-flow ratio, angle of inlet compression, angle of attack, and Mach number.
Date: February 23, 1956
Creator: Hasel, Lowell E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration

Description: Report presenting an investigation of a swept-wing supersonic bomber configuration in the 4- by 4-foot supersonic pressure tunnel. Testing occurred at Mach numbers of 1.41 and 2.01 and a designated Reynolds number based on the wing mean aerodynamic chord. The model had a tapered wing with an aspect ratio of 3.5, a taper ratio of 0.2, a thickness ratio of 5.5 percent and 47 degrees sweep of the quarter-chord line. The investigation included the longitudinal and lateral force characteristics and ā€¦ more
Date: February 1, 1956
Creator: Smith, Norman F. & Hasel, Lowell E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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As Investigation at Mach Numbers of 1.41 and 2.01 of the Aerodynamic Characteristics of an 0.025-scale Model of the MX-1712

Description: "An investigation of the aerodynamic characteristics of an 0.025-scale model of the MX-1712 configuration has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel. The tests were performed at Mach numbers of 1.41 and 2.01 at a Reynolds number of approximately 2.6 x 10(exp 6) based on the wing mean aerodynamic chord. The MX-1712 is a proposed swept-wing, jet-powered supersonic bomber aircraft. The wing is of aspect ratio 3.5, taper ratio 0.2, and thickness ratio 5.5 percent (strā€¦ more
Date: October 17, 1952
Creator: Smith, Norman F. & Hasel, Lowell E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach Numbers of 1.62, 1.93, and 2.41 of the Effect of Oscillation Amplitude on the Damping in Pitch of Delta-Wing-Body Combinations

Description: Report presenting testing of four delta-wing and body combinations at specified Mach numbers to determine the effect of oscillation amplitude on the damping in pitch. The body tested was the same, but the wings had 25 degree, 30 degree, 35 degree, and 45 degree semiapex angles. Results indicate that the damping-in-pitch parameter can be predicted by theory, and when a variation of this parameter with amplitude occurs, it is usually small and camping increases with decreasing amplitude.
Date: October 26, 1953
Creator: Henderson, Arthur, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation at Mach Numbers of 1.62 and 1.93 of the Lift Effectiveness and Integrated Downwash Characteristics of Several In-Line Missile Configurations Having Equal-Span Wings and Tails

Description: Memorandum presenting an investigation made at Mach numbers of 1.62 and 1.93 to determine the lift effectiveness and average downwash characteristics of several in-line missile configurations with rectangular and triangular tail plan forms. Breakdown tests were made for combinations of a body and four wing plan forms and two tail plan forms. Results regarding lift and drag results, pitching-moment results, and integrated downwash effects are provided.
Date: April 11, 1952
Creator: Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach Numbers to 1.04 of Blade-Loading Characteristics of Two Full-Scale Three-Blade Supersonic Propellers Differing in Blade-Section Camber

Description: Memorandum presenting total-pressure surveys made in the slipstreams of two full-scale three-blade supersonic propellers in the 16-foot transonic tunnel at Mach numbers up to 1.04 to determine the effects of camber on supersonic-propeller characteristics. The two propellers were similar except that one of them had symmetrical blade sections and the other had cambered blade sections and a slightly different pitch distribution. Over the complete range of the tests, the cambered propeller maintainā€¦ more
Date: September 12, 1957
Creator: Salters, Leland B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation at subsonic speeds of several modifications to the leading-edge region of the NACA 64A010 airfoil section designed to increase maximum lift

Description: Report presenting three modifications to the leading-edge region of the NACA 64A010 airfoil section, which were designed and tested two-dimensionally at both low and high subsonic speeds. The modifications increased the low-speed maximum lift coefficient of the symmetrical reference section, largely by increasing the angle of attack at which stall occurred.
Date: December 1956
Creator: Maki, Ralph L. & Hunton, Lynn W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation at Subsonic Speeds of the Rolling Effectiveness of a Small Perforated Spoiler on a Wing Having 45 Degrees of Sweepback

Description: Memorandum presenting an investigation of the rolling effectiveness of a partial-span, perforated spoiler on a wing with 45 degrees of sweepback at Mach numbers from 0.25 to 0.96. The effects of the spoiler on the lift, drag, and pitching moment were also determined. Results regarding Reynolds number, Mach number, and predicted rate of roll are provided.
Date: September 15, 1952
Creator: Bandettini, Angelo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at supersonic speed (M = 1.53) of the pressure distribution over a 63 degrees swept airfoil of biconvex section at several angles of attack

Description: Report presenting the results of an investigation at supersonic speed of the distribution of pressure over the surface of a swept airfoil of biconvex section at various angles of attack. The measurements are compared with supersonic lifting-surface theory, which generally indicated good agreement except over the regions of the airfoil influenced by the subsonic trailing edge and the tips. Results regarding the pressure distribution, boundary-layer studies, and normal force and pitching moment aā€¦ more
Date: September 24, 1948
Creator: Katzen, Elliott D.; Frick, Charles W. & Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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