Technical Report Archive & Image Library (TRAIL) - 32,509 Matching Results

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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.
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 maintain… more
Date: September 12, 1957
Creator: Salters, Leland B., Jr.
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.
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
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 a… more
Date: September 24, 1948
Creator: Katzen, Elliott D.; Frick, Charles W. & Boyd, John W.
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 zero lift

Description: Report presenting an investigation of the distribution of pressure at zero lift over the surface of a swept airfoil of biconvex section. The measured pressures are compare with theoretical values calculated from thin-airfoil theory. Results regarding pressure distributions, drag, and boundary-layer studies are provided.
Date: June 10, 1948
Creator: Frick, Charles W. & Boyd, John W.
Partner: UNT Libraries Government Documents Department
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Investigation at supersonic speeds of a translating-spike inlet employing a steep-lip cowl

Description: Report presenting an experimental investigation conducted in the supersonic wind tunnel at three Mach numbers on a translating-spike inlet analytically designed to keep the cone shoulder downstream of the cowl-lip station without a net internal contraction. The inlet in this investigation had an internal cowl-lip angle of 17.5 degrees and was constructed to have the same inlet capture area and maximum cross-sectional area as a previously tested inlet with an internal cowl-lip angle of only 7 de… more
Date: October 11, 1954
Creator: Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department
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Investigation at supersonic speeds of an inlet employing conical flow separation from a probe ahead of a blunt body

Description: Report presenting an investigation in the supersonic wind tunnel on an inlet employing conical flow separation from a probe extending upstream from a hemispherical-nosed centerbody. Pressure-recovery and drag characteristics for the inlet were very nearly comparable with a conical-spike inlet, but compared less favorably at Mach numbers below 2.0. A large reduction in pressure recovery and mass flow was obtained at angle of attack.
Date: January 19, 1953
Creator: Hearth, Donald P. & Gorton, Gerald C.
Partner: UNT Libraries Government Documents Department
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Investigation at supersonic speeds of external-drag effects and pumping characteristics of a short ejector

Description: Report presenting an investigation at free-stream Mach numbers of 1.62, 1.94, and 2.41 to determine the external-drag effects and pumping characteristics of a short ejector housed within a highly bottailed afterbody. The tests covered secondary to primary diameter ratios of 1.50 and 1.33, mass flow ratios from 0 to 0.20, and a sonic and a supersonic primary nozzle. Results regarding drag and pumping characteristics are provided.
Date: June 14, 1955
Creator: Love, Eugene S. & O'Donnell, Robert M.
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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Investigation at Supersonic Speeds of the Effect of Jet Mach Number and Divergence Angle of the Nozzle Upon the Pressure of the Base Annulus of a Body of Revolution

Description: Report presenting an investigation in the 9-inch supersonic tunnel to determine the jet effects for varying jet Mach number and nozzle divergence angle upon the pressure on the base annulus of a model with a cylindrical afterbody. Testing occurred over a wide range of jet static pressure ratios and Mach numbers. Results regarding sonic jets and supersonic jets are provided.
Date: December 17, 1954
Creator: Bromm, August F., Jr. & O'Donnell, Robert M.
Partner: UNT Libraries Government Documents Department
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An Investigation at Supersonic Speeds of the Effect of Varying the Maximum-Thickness Position Upon the Aerodynamic Characteristics of a Series of 3 1/2-Percent-Thick Delta Wings

Description: Report presenting a wind-tunnel investigation on 3.5-percent-thick symmetrical double-wedge delta wings to determine the effects of thickness distribution on lift, drag, and pitching moment. Six maximum-thickness positions were tested on three basic wings at different Mach numbers and Reynolds numbers. Results regarding lift, drag, the lift-drag ratio, and the center of pressure are provided.
Date: August 9, 1955
Creator: Mueller, James N.
Partner: UNT Libraries Government Documents Department
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Investigation at Supersonic Speeds of the Effects of Bomb-Bay Configuration Upon the Aerodynamic Characteristics of Fuselages With Noncircular Cross Sections

Description: Memorandum presenting an investigation in the 9-inch supersonic tunnel to ascertain the lift, drag, and pitching moments of typical body-bomb-bay configurations with and without the bomb. The bodies had elliptical, triangular, and teardrop cross sections. Results regarding effects of angle-of-attack variation and effects of Mach number variation are provided.
Date: November 29, 1956
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department
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Investigation at Supersonic Speeds of the Variation With Reynolds Number and Mach Number of the Total, Base, and Skin-Friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag

Description: Results are presented from an investigation of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag of seven boattail bodies of revolution designed for minimum wave drag according to the theory of NACA-TN-2550. The tests covered a Reynolds number range from approximately 1.0 x 10(6) to 10.0 x 10(6) at Mach numbers of 1.62, 1.93, and 2.41 respectively.
Date: June 1956
Creator: Bromm, August F., Jr. & Goodwin, Julia M.
Partner: UNT Libraries Government Documents Department
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Investigation at supersonic speeds of the wave drag of seven boattail bodies of revolution designed for minimum wave drag

Description: Report presenting an investigation in the 9-inch supersonic tunnel to determine the effects of varying Reynolds number at each of three Mach numbers on the wave drag of seven boattail bodies of revolution designed for minimum wave drag. Results indicated that there was little variation in the pressure distribution with Reynolds number. Results regarding pressure distributions and wave drag are provided.
Date: December 1953
Creator: Bromm, August F., Jr. & Goodwin, Julia M.
Partner: UNT Libraries Government Documents Department
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Investigation at Transonic Speeds of a Forward-Located Underslung Air Inlet on a Body of Revolution

Description: Report presenting an investigation in the transonic tunnel to determine the flow phenomena, pressure recovery, and external drag of a forward-located underslung air scoop mounted on a basic body of revolution with fineness ratio 11, which when cut off to provide an exit for the internal flow had a fineness ratio of 8. Results regarding the surface pressure distributions, drag, lift and pitching moment, and flow into the inlet on the modified model are provided.
Date: January 29, 1953
Creator: Pierpont, P. Kenneth & Braden, John A.
Partner: UNT Libraries Government Documents Department
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Investigation at Transonic Speeds of Aerodynamic Characteristics of a Semicircular Air Inlet in the Root of a 45 Degree Sweptback Wing

Description: Report presenting an investigation in the transonic blowdown tunnel at Mach numbers from 0.63 to 1.41 to determine increments in lift, drag, and pitching moment of a sweptback semicircular air inlet installed in the root of a 45 degree sweptback wing. Results regarding internal pressures and inlet performances are provided.
Date: March 23, 1955
Creator: Trescot, Charles D., Jr. & Keith, Arvid L., Jr.
Partner: UNT Libraries Government Documents Department
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Investigation at transonic speeds of aerodynamic characteristics of a semielliptical air inlet in the root of a 45 degree sweptback wing

Description: Report presenting an investigation in the transonic blowdown tunnel at a range of Mach numbers to determine the increments in lift, drag, and pitching moments due to the installation of a semielliptical-shaped air inlet in the root of a 45 degree sweptback wing and to study the internal flow characteristics of the inlet. Results regarding the internal pressure measurements, effect of inlet installation on external aerodynamic characteristics, effect of boundary-layer removal on internal pressur… more
Date: December 11, 1953
Creator: Howell, Robert R. & Trescot, Charles D., Jr.
Partner: UNT Libraries Government Documents Department
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Investigation at transonic speeds of deflectors and spoilers as gust alleviators on a 35 degree swept wing: transonic bump method

Description: Report presenting an investigation in the high-speed 7- by 10-foot tunnel using the transonic bump method to determine the gust-alleviation capabilities of spoilers and deflectors when mounted on a 35 degree swept semispan wing with NACA 65A006 airfoil sections. Testing was conducted over a range of Mach numbers and angles of attack.
Date: June 1957
Creator: Croom, Delwin R. & Huffman, Jarrett K.
Partner: UNT Libraries Government Documents Department
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Investigation at transonic speeds of loading over a 30 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section mounted on a body

Description: Report presenting the aerodynamic load characteristics for a wing-body combination for a range of Mach numbers and angles of attack. Two wings with the same dimensions but different types of construction (one of solid steel, one of plastic with an inner steel core) were tested. Results regarding flow studies, chordwise pressure distributions, spanwise load distributions, panel loads, center of loads, and twist distribution are provided.
Date: September 26, 1957
Creator: Arabian, Donald D.
Partner: UNT Libraries Government Documents Department
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An Investigation at Transonic Speeds of the Aerodynamic Characteristics of an Air Inlet Installed in the Root of a 45 Degree Sweptback Wing

Description: Report presenting an investigation in the transonic blowdown tunnel from Mach numbers 0.80 to 1.41 to determine the increments in lift and drag due to installation of a triangular-shaped air inlet in the root of a 45 degree sweptback wing and to determine the internal flow characteristics of the inlet. Results regarding pressure measurements of the inlet model, force measurements of basic and inlet models, and effect of boundary-layer bypass scoop and fuselage nose configuration on characterist… more
Date: October 1, 1952
Creator: Howell, Robert R. & Keith, Arvid L., Jr.
Partner: UNT Libraries Government Documents Department
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Investigation at Transonic Speeds of the Effect of a Positive-Lift Balancing Tab on the Hinge-Moment and Lift-Characteristics of a Full-Span Flap on a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3

Description: Report presenting an investigation at transonic speeds to determine the control characteristics of a linked tab and flap. The control device consisted of an auxiliary lifting surface (tab) mounted on the end of a boom which was linked to a full-span flap. The tab was found to be capable of reducing the flap hinge moment to zero through the angle of attack and Mach number range tested.
Date: November 20, 1952
Creator: Lockwood, Vernard E. & Fikes, Joseph E.
Partner: UNT Libraries Government Documents Department
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An Investigation at Transonic Speeds of the Effects of Control Chord and Span on the Control Characteristics of a Tapered Wedge-Type Wing of Aspect Ratio 2.5: Transonic-Bump Method

Description: Report presenting an investigation to determine the control characteristics of flap-type controls of various chords and spans on an unswept wing with a modified double-wedge section, an aspect ratio of 2.5, and a taper ratio of 0.625.The control chords in the study were 25, 35, and 45 percent of the wing chord, and the control spans were 25, 50, and 75 percent of the wing semispan. The data from the study indicated that the control-parameter values are approximately proportional to control chor… more
Date: September 20, 1951
Creator: Vogler, Raymond D.; Lockwood, Vernard E. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department
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An Investigation at Transonic Speeds of the Effects of Fences, Drooped Nose, and Vortex Generators on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a 6-Percent-Thick, 45 Degree Sweptback Wing

Description: Report presenting an investigation at transonic speeds to determine the effects of fences, drooped nose, combination fences and drooped nose, and vortex generators on a 45 degree sweptback wing-fuselage combination. The purpose of undertaking this investigation was due to the pitch-up tendency that results from leading-edge vortex-type flow on thin sweptback wings. The data for each component and their interaction with one another is also provided.
Date: March 31, 1953
Creator: Hieser, Gerald
Partner: UNT Libraries Government Documents Department
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