Serial/Series Title
Country
States
1,181 Matching Results
Results open in a new window/tab.
Results:
1 - 24 of
1,181
next
Experiments With an Airfoil Model on Which the Boundary Layers Are Controlled Without the Use of Supplementary Equipment
This report describes test made in the Variable Density Wind Tunnel of the NACA to determine the possibility of controlling the boundary layer on the upper surface of an airfoil by use of the low pressure existing near the leading edge. The low pressure was used to induce flow through slots in the upper surface of the wing. The tests showed that the angle of attack for maximum lift was increased at the expense of a reduction in the maximum lift coefficient and an increase in the drag coefficient.
Date:
April 1931
Creator:
Abbott, Ira H.
System:
The UNT Digital Library
Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine
Report presenting a flight investigation to determine the comparative performance of AN-F-58 and AN-F-32 fuels in a 4000-pound-thrust turbojet engine. The fuels were equivalent over the range of conditions investigated. Results regarding corrected net thrust, corrected jet-fuel consumption, variation of corrected tail-pipe temperature, combustor blow-out speeds, and visual observations of the jet exhaust are provided.
Date:
April 7, 1949
Creator:
Acker, Loren W. & Kleinknecht, Kenneth S.
System:
The UNT Digital Library
Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method
"A 1/12-scale model of a horizontal tail of a fighter airplane was tested through the transonic speeds in the high-speed flow over an airplane wing, the surface of which served as a reflection plane for the model. Measurements of lift, elevator-hinge moment, angle of attack, and elevator angle were made in the Mach number range from 0.75 to 1.04 for elevator deflections ranging from 10 degrees to minus 10 degrees, and for angles of attack of minus 1.2 degrees, 0.4 degrees, and 3.4 degrees. The equipment used to measure the hinge moments of the model proved to be unsatisfactory, and for this reason the hinge-moment data are considered to be only qualitative" (p. 1).
Date:
April 11, 1947
Creator:
Adams, Richard E. & Silsby, Norman S.
System:
The UNT Digital Library
Drag Measurements of a Swept-Back Wing Having Inverse Taper as Determined by Flight Tests at Supersonic Speeds
Report discussing the results of flight tests to determine the drag at zero lift of a swept-back wing of inverse taper using an NACA 65-009 airfoil. The data was compared to untapered wings with a similar degree of sweepback. The tapered wing was found to have a lower drag coefficient than the 34-degree swept-back untapered wing but a higher drag coefficient than the 45-degree swept-back untapered wing.
Date:
April 8, 1947
Creator:
Alexander, Sidney R.
System:
The UNT Digital Library
Flight Tests to Determine the Drag of Fin-Stabilized Parabolic Bodies at Transonic and Supersonic Speeds
Report presenting testing on parabolic bodies of revolution of two fineness ratios in the transonic and supersonic range. One had a body fineness ratio of 7.87 and one had a ratio of 12 and were tested under different Mach number ranges. Experimental results and drag estimates of various portions of the body are provided.
Date:
April 21, 1948
Creator:
Alexander, Sidney R.; Chauvin, Leo T. & Rumsey, Charles B.
System:
The UNT Digital Library
Experimental Static Aerodynamic Forces and Moments at Low Speed on a Canard Missle During Simulated Launching From the Midsemispan and Wing-Tip Locations of a 45 Degree Sweptback Wing-Fuselage Combination
Report presenting an investigation at low speed to determine the static aerodynamic forces and moments on a canard missile model during launching from the midsemispan and wing-tip locations of a wing-fuselage combination with a 45 degree sweptback wing. When the missile was mounted under the wing at the midsemispan location, changes in chordwise position produced large changes in missile forces and moments.
Date:
April 6, 1955
Creator:
Alford, William J., Jr.
System:
The UNT Digital Library
Investigation at high subsonic speeds of finned and unfinned bodies mounted at various locations from the wings of unswept- and swept-wing--fuselage models, including measurements of body loads
Report presenting an investigation to determine the effects of location of bodies (finned and unfinned) on the aerodynamic characteristics of unswept- and swept-wing--fuselage models and to determine the aerodynamic loads on the bodies in the presence of the wings. Results for the complete model characteristics and for the body are provided.
Date:
April 1, 1954
Creator:
Alford, William J., Jr. & Silvers, H. Norman
System:
The UNT Digital Library
Determination of vortex paths by series expansion technique with application to cruciform wings
Report presenting a series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge.
Date:
April 1956
Creator:
Alksne, Alberta Y.
System:
The UNT Digital Library
A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds
From Summary: "A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer."
Date:
April 28, 1953
Creator:
Allen, H. Julian & Eggers, A. J., Jr.
System:
The UNT Digital Library
The interaction of boundary layer and compression shock and its effect upon airfoil pressure distributions
Report presenting an investigation of the mechanism of interaction of compression shock with boundary layer. Shockless pressure distributions at supercritical Mach numbers were found to be accounted for by a marked thickening of the boundary layer for some distance ahead of a shock wave.
Date:
April 10, 1947
Creator:
Allen, H. Julian; Heaslet, Max A. & Nitzberg, Gerald E.
System:
The UNT Digital Library
The Effect of Blade-Section Camber on the Stall-Flutter Characteristics of Three NACA Propellers at Zero Advance
Report presenting an investigation to determine the effect of blade-section camber on the stall-flutter characteristics of three propellers using a 6000-horsepower propeller dynamometer. Up to a certain blade angle, there was an increase in flutter-speed coefficient with an increase in blade-section design lift coefficient. An increase in thrust was found to lead to an increase in tip Mach number in the flutter region of the propeller blades.
Date:
April 6, 1953
Creator:
Allis, Arthur E. & Swihart, John M.
System:
The UNT Digital Library
Chordwise and Spanwise Loadings Measured at Low Speed on Large Triangular Wings
Report presenting pressure distributions of three triangular wing models: a wing-alone model, the same wing combined with a body, and a mock-up of a triangular-wing airplane. Results regarding the separation-vortex air flow over triangular wings, general comments regarding the applicability of the study, chordwise pressure distribution, section lift characteristics, center of pressure, and span load distribution are provided.
Date:
April 19, 1949
Creator:
Anderson, Adrien E.
System:
The UNT Digital Library
Tests of NACA 65(216)-420 and 66(218)-420 Airfoils at High Speeds
Report presenting wind tunnel tests of NACA 65(216)-420 and 66(218)-420 airfoils at speeds up to and slightly above the critical. Section coefficients of lift, drag, and pitching-moment and extensive pressure-distribution data are presented. The critical speed for these airfoils at their design life coefficient of 0.4 is shown to be about 460 miles per hour at seal level and about 415 miles per hour at 25,000 feet altitude.
Date:
April 10, 1944
Creator:
Anderson, Joseph L.
System:
The UNT Digital Library
High-Speed Wind-Tunnel Tests of a Twin-Fuselage Pursuit Airplane
Report discussing the aerodynamic characteristics of a twin-fuselage pursuit airplane model, especially at high speeds. Information about the force data and critical Mach numbers for parts of the model is provided. Suggestions for increasing the Mach number of divergence by making modifications to the wing-fuselage fillets and external shape of the radiator are also included.
Date:
April 24, 1946
Creator:
Anderson, Joseph L. & Tkac, Victor B.
System:
The UNT Digital Library
Flight measurements of the wing-dropping tendency of a straight-wing jet airplane at high subsonic Mach numbers
From Summary: "Flight tests were conducted on a straight-wing fighter-type jet airplane to investigate the lateral-control characteristics associated with a wing-dropping tendency encountered at high subsonic Mach numbers. The chief factors found to account directly for the wing-dropping tendency were a progressive reduction in aileron-control effectiveness with increasing Mach number, and an increase in effective dihedral above a Mach number of 0.8 which made the lateral trim particularly sensitive to small changes in sideslip angle."
Date:
April 24, 1951
Creator:
Anderson, Seth B.; Ernst, Edward A. & Van Dyke, Rudolph D., Jr.
System:
The UNT Digital Library
Investigation of Certain Wing Shapes With Sections Varying Progressively Along the Span
This investigation has a double object: 1) the calculation of the general characteristics of certain wings with progressively varying sections; 2) the determination of data furnishing, in certain cases, some information on the actual distribution of the external forces acting on a wing. We shall try to show certain advantages belonging to the few wing types of variable section which we shall study and that, even if the general aerodynamic coefficients of these wings are not often clearly superior to those of certain wings of uniform section, the wings of variable section nevertheless have certain advantages over those of uniform section in the distribution of the attainable stresses.
Date:
April 1931
Creator:
Arsandaux, L.
System:
The UNT Digital Library
Investigation of the effect of velocity diagram on inlet total-pressure distortions through single-stage subsonic axial-flow compressors
Memorandum presenting a preliminary and theoretical investigation of the effect of velocity diagram on inlet total-pressure distortions through single-stage subsonic axial-flow compressors for incompressible flow. A theoretical investigation was used to determine proper velocity diagrams and then the wake of a 1/4-inch-diameter rod was measured upstream of the rotor. The tests indicated that the derived equation will estimate the downstream distortion with reasonable accuracy for inlet total-pressure distortion which extends far enough circumferentially to alter the static-pressure field in the blade passage.
Date:
April 17, 1957
Creator:
Ashby, George C., Jr.
System:
The UNT Digital Library
Turbulent Shearing Stress in the Boundary Layer of Yawed Flat Plates
Note presenting hot-wire anemometer measurements of the turbulent shearing stress in a turbulent boundary layer on a yawed flat plate. The measured velocity profiles are used to calculate the shear distribution and the result is compared with the result of experimental shear measurements.
Date:
April 1958
Creator:
Ashkenas, Harry
System:
The UNT Digital Library
Investigation of the Turbulent Boundary Layer on a Yawed Flat Plate
Note presenting the problem of the effect of yaw on the turbulent boundary layer and skin friction of infinite cylinders, which is reviewed and compared with the case of laminar flow. The conclusion indicates that present understanding of the mechanism of turbulent shear does not permit exhaustion of two-dimensional data even to this elementary case of three-dimensional flow. Results regarding pressure distributions, two-dimensionality and flow direction, velocity profiles, virtual origin, virtual origin for yawed plates, boundary-layer growth, and the results obtained by Young and Booth are provided.
Date:
April 1955
Creator:
Ashkenas, Harry & Riddell, Frederick R.
System:
The UNT Digital Library
Ground Simulator Studies of a Small Side-Located Controller in a Power Control System
Memorandum presenting an investigation to determine the operating characteristics of a small side-located control stick with the use of a ground simulator incorporating a power control system. The simulator or pitch chair was designed to produce the pitching motion associated with the short-period mode of an airplane. The general opinion of all of the pilots operating the pitch chair was that they were favorably impressed with their ability to precisely track with the small side-located controller provided the control-system characteristics were desirable.
Date:
April 23, 1958
Creator:
Assadourian, Arthur
System:
The UNT Digital Library
A Summary and Analysis of Wind-Tunnel Data on the Lift and Hinge-Moment Characteristics of Control Surfaces Up to a Mach Number of 0.90
Report presenting an extensive collection of lift and hinge-moment characteristics of control surfaces up to a Mach number of 0.90 in a high-speed wind tunnel. A wide variety of control-surface profiles, plan forms, and aerodynamic balances are included. Results regarding elevator hinge moments and longitudinal control, aileron hinge moments and lateral control, control-surface characteristics, and transonic flutter are highlighted.
Date:
April 30, 1948
Creator:
Axelson, John A.
System:
The UNT Digital Library
Flight investigation of the performance and cooling characteristics of a long-nose high-inlet-velocity cowling on the XP-42 airplane
Report presenting the results of a series of flight tests of the maximum speed and cooling characteristics in high-speed level flight and in climb of the XP-42 airplane equipped with a long-nose high-inlet-velocity cowling. The results indicated that a maximum speed of 338 miles per hour at 870 horsepower at 17,000 feet was achievable, which is above the engine critical altitude. Pressure measurements in the entrances in the cylinder baffles showed a uniform distribution of pressure on the front of the engine in high-speed level flight and a fairly uniform distribution in full-power climb.
Date:
April 1942
Creator:
Bailey, F. J., Jr.; Johnston, J. Ford & Voglewede, T. J.
System:
The UNT Digital Library
Coefficient of friction and damage to contact area during the early stages of fretting 2: steel, iron, iron oxide, and glass combinations
Report presenting experiments to study the start of fretting and cause of damage during the early stages of fretting of steel-steel combinations at a frequency 5 cycles per minute, an amplitude of 0.006 inch, a load of 150 grams, in air with relative humidity of less than 10 percent. Pure iron, glass, and iron oxide powder compacts were used in supplementary experiments.
Date:
April 1954
Creator:
Bailey, John M. & Godfrey, Douglas
System:
The UNT Digital Library
Flight Measurements at Transonic Speeds of the Buffeting Characteristics of the XF-92A Delta-Wing Research Airplane
Report presenting testing on a 60 degree delta-wing XF-92A airplane at a variety of Mach numbers to obtain measurements regarding buffet-induced fluctuations in normal acceleration and of fluctuations in structural shear load of the left wing. The altitudes tested ranged from 25,000 to 38,000 feet. Results regarding the buffet boundary, wing flow conditions, buffet frequencies, buffet intensities, and a comparison to buffeting of other airplanes are provided.
Date:
April 28, 1955
Creator:
Baker, Thomas F. & Johnson, Wallace E.
System:
The UNT Digital Library