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Flight Investigation of the Effect of Thickening the Aileron Trailing Edge on Control Effectiveness for Sweptback Tapered Wings Having Sharp-and Round-Nose Sections
Report discussing an investigation of the rolling effectiveness at transonic and supersonic speeds on a 38.1 degree sweptback tapered wing with NACA 0010-64 airfoil sections and partial-span ailerons of true contour with a modified flt-side blunt trailing-edge shape. The variation of Reynolds number with Mach number and the control effectiveness is provided.
Date:
May 2, 1950
Creator:
Strass, H. Kurt & Fields, Edison M.
Object Type:
Report
System:
The UNT Digital Library
Free-Jet Investigation of a 16-Inch Ram Jet at Mach Numbers of 1.35, 1.50, and 1.73
Memorandum presenting the results of a free-jet investigation to determine the internal performance of a 16-inch ram jet. Data were obtained at a range of altitudes and Mach numbers. Results regarding the rake flame holder, effect of fuel injector on burner performance, effect of propylene oxide on burner performance, serrated annular baffle flame holder, diffuser performance, and performance at off-design spike location are provided.
Date:
October 2, 1950
Creator:
Wilcox, Fred; Baker, Sol & Perchonok, Eugene
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements of the Effects of Surface Condition on the Supersonic Drag of Fin-Stabilized Parabolic Bodies of Revolution
Report presenting testing of rocket-powered models at supersonic speeds to determine some of the surface conditions on the zero-lift drag of fin-stabilized parabolic bodies of revolution. Two types of models and three types of surface roughness were tested. Results regarding mean-drag coefficients, side-pressure coefficients, and total-drag coefficients are provided.
Date:
May 2, 1952
Creator:
Jackson, H. Herbert
Object Type:
Report
System:
The UNT Digital Library
Free-Flight Investigation of the Zero-Lift Drag of Several Wings at Supersonic Mach Numbers Extending to 2.6
Report presenting testing of the zero-lift drag of several wings at supersonic Mach numbers. The delta wings had the lowest drag over the entire Mach number range. Results regarding the variation of Reynolds number with Mach number, total drag coefficient, wing-plus-interference drag coefficients, and skin friction drag are provided.
Date:
December 2, 1952
Creator:
Hopko, Russell N. & Sandahl, Carl A.
Object Type:
Report
System:
The UNT Digital Library
Experimental Investigation of the Static Aerodynamic and Dynamic Damping-in-Roll Characteristics of an 8-Cm Aircraft Rocket With Solid and Slotted Fins
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.
Object Type:
Report
System:
The UNT Digital Library
The effects on the aerodynamic characteristics of varying the wing thickness ratio of a triangular wing-body configuration at transonic speeds from tests by the NACA wing-flow method
Testing occurred using the NACA wing-flow method at a range of Mach numbers to determine the aerodynamic characteristics of three triangular wing-fuselage models which differed only in wing thickness-chord ratio. The wings had an aspect ratio of 2.31 with 6-, 9-, and 12-percent-thick biconvex sections and a fuselage with a fineness ratio of 12. Results regarding the normal force, chord force, and pitching moment for various angles of attack.
Date:
April 2, 1952
Creator:
Hall, Albert W. & McKay, James M.
Object Type:
Report
System:
The UNT Digital Library
Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.70 to 1.37 of Rocket-Propelled Models Having a Modified Triangular Wing
"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.
Object Type:
Report
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane triangular wing of aspect ratio 2 with NACA 0003-63 section
Report presenting testing of a wing-body combination with a plane triangular wing of aspect ratio 2 and NACA 0003-63 sections in streamwise planes at subsonic and supersonic Mach numbers. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date:
February 2, 1951
Creator:
Heitmeyer, John C. & Smith, Willard G.
Object Type:
Report
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution, cambered and twisted for trapezoidal span load distribution
"A wing-body combination having a triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution in streamwise planes, and cambered and twisted for a trapezoidal span distribution has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.25 to 0.96 and 1.20 to 1.70 at a Reynolds number of 1.5 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers" (p. 1).
Date:
February 2, 1951
Creator:
Phelps, E. Ray & Smith, Willard G.
Object Type:
Report
System:
The UNT Digital Library
Preliminary evaluation of the air and fuel specific-impulse characteristics of several potential ram-jet fuels 2: magnesium and magnesium - octene-1 slurries
Report presenting a preliminary analytical evaluation of the air and fuel specific-impulse characteristics of magnesium and magnesium-octene-1 slurries. Adiabatic combustion flame temperature, air specific impulse, and fuel-weight specific impulse are given for each fuel.
Date:
May 2, 1951
Creator:
Gammon, Benson E.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds
From Introduction: "An investigation of the high-speed aerodynamic characteristics of a modified delta wing in combination with a fuselage was conducted in the Langley high-speed 7- by 10-foot tunnel. The model was tested on the sting support system through a Mach number range of 0.40 to 0.90 with both free and fixed transition. Because of the nature of the transition effect, the results seemed to be of the general interest and are presented in the present paper."
Date:
May 2, 1950
Creator:
Polhamus, Edward C. & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Analysis of several methods of pumping cooling air for turbojet engine afterburners
From Introduction: "Afterburning is well established as an effective means of increasing the thrust of a turbojet engine. In order to obtain the maximum thrust from an afterburner, it is necessary to burn to the highest temperatures possible (reference 1). At these high temperatures, material limitations (reference 2) necessitate the installation of cooling systems to permit safe and reliable operation."
Date:
February 2, 1953
Creator:
Samuels, John C. & Yanowitz, Herbert
Object Type:
Report
System:
The UNT Digital Library
Effects of Additives on Corrosion and Mass Transfer in Sodium Hydroxide - Nickel Systems Under Free-Convection Conditions
Memorandum presenting a study of the effect of additives on the extent of corrosion and mass transfer in sodium hydroxide - "L" nickel systems. The extent of corrosion and mass transfer was determined by a measurement of the weight change of a specimen in the hot zone, and by metallographic examination of the specimen cross section. Results regarding the reproducibility, appearance of specimens, and additives having a detrimental effect, no effect, or a beneficial effect are provided.
Date:
August 2, 1954
Creator:
Forestieri, Americo F.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Experiments with Pilot Burners for Ram-Jet Combustors
Memorandum presenting a preliminary development program on can-type pilot burners as part of an overall program to develop a high-altitude, low-drag ramjet combustor. Results regarding single-row circular pilot burners, six-row circular pilot burners, and annular-segment pilot burners are provided.
Date:
January 2, 1953
Creator:
Farley, John M.; Smith, Robert E. & Povolny, John H.
Object Type:
Report
System:
The UNT Digital Library
Flame velocities of propane- and ethylene-oxygen-nitrogen mixtures
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.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a 68.4 degree delta wing at Mach numbers of 1.6 and 1.9 over a wide Reynolds number range
From Introduction: "The purpose of this paper is to provide further information on the effects of Reynolds number on the aerodynamic characteristics of the wing of reference 1 as well as to provide load distributions for the wing at Mach numbers of 1.6 and 1.9."
Date:
November 2, 1953
Creator:
Hatch, John E., Jr. & Gallagher, James J.
Object Type:
Report
System:
The UNT Digital Library
Preflight Tests and Flight Performance of a 6.5-Inch Diameter Ram-Jet Engine
Report presenting testing of a 20 degree semiangle conical-inlet ramjet engine with a design Mach number of 2.13 in free supersonic jets to determine the inlet and combustion performance over a fuel-air ratio and Mach number range. Results regarding preflight and flight testing are provided.
Date:
November 2, 1953
Creator:
Hinners, Arthur H., Jr. & Foland, Douglas H.
Object Type:
Report
System:
The UNT Digital Library
Low-speed static stability and control characteristics of a 1/4-scale model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4, unswept wing
Report presenting an investigation in the Langley 300 mph tunnel to determine the low-speed static stability and control characteristics of a model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4 wing. Tests were also made to determine optimum flap deflection for a slotted flap. Results regarding longitudinal stability and control, high lift devices, lateral and directional stability, and lateral and directional control are provided.
Date:
November 2, 1953
Creator:
Moseley, William C., Jr. & Taylor, Robert T.
Object Type:
Report
System:
The UNT Digital Library
Effects of sweepback and taper on the force and cavitation characteristics of aspect-ratio-4 hydrofoils
Report presenting an investigation to determine the effects of sweepback and taper ratio on the cavitation and hydrodynamic force characteristics of hydrofoils. Four hydrofoils were used, all of which had different taper ratios and degrees of sweep. Results regarding the effect of cavitation on hydrodynamic characteristics, effect of sweep on cavitation and force characteristics, effect of taper ratio on cavitation and force characteristics, and a comparison with wind-tunnel data are provided.
Date:
December 2, 1952
Creator:
King, Douglas A. & Land, Norman S.
Object Type:
Report
System:
The UNT Digital Library
Prediction of flame velocities of hydrocarbon flames
Report presenting some laminar-flame-velocity data surveyed with respect to the correspondence between experimental flame velocities and values predicted by semitheoretical and empirical methods.
Date:
January 2, 1953
Creator:
Dugger, Gordon L. & Simon, Dorothy M.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a trailing-edge paddle-control surface on a triangular wing of aspect ratio 2 at subsonic and supersonic speeds
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.
Object Type:
Report
System:
The UNT Digital Library
Comparison of Experimental Hydrodynamic Impact Loads and Motions for a V-Step and a Transverse-Step Hydro-Ski
Report presenting a comparison of the hydrodynamic impact loads and motions encountered in testing a V-step and a transverse-step flat-bottom hydro-ski with beam loadings of about 4.5. Testing occurred in smooth water over a range of velocities, flight-path angles, and fixed trims. Results regarding time histories of draft, vertical velocity, and vertical acceleration, impact lift coefficient, draft coefficient, and time coefficient for rebound are provided.
Date:
February 2, 1954
Creator:
Miller, Robert W.
Object Type:
Report
System:
The UNT Digital Library
The Use of Area Suction for the Purpose of Improving Trailing-Edge Flap Effectiveness on a 35 Degree Sweptback Wing
"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.
Object Type:
Report
System:
The UNT Digital Library
Effect of Wedge-Type Boundary-Layer Diverters on Performance of Half-Conical Side Inlets at Mach Number 2.96
Report presenting an investigation at Mach number 2.96 to study the effects of wedge-type boundary-layer removal on the performance of side inlets with half of a double-conical external-compression surface. Some of the parameters investigated were the wedge height, wedge inclined angle, wedge-tip position, and splitter-plate geometry. Two lengths of constant-area diffuser throat section were also considered.
Date:
August 2, 1954
Creator:
Johnson, Harry W. & Piercy, Thomas G.
Object Type:
Report
System:
The UNT Digital Library