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985 Matching Results
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Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section
Report presenting tests in the two-dimensional low-turbulence pressure tunnel to study the interference effects of various pusher-propeller shaft-housing combinations on a low-drag airfoil. Thirty different combinations were tested, variations being made in shaft size, shape, angle, and fillet.
Date:
November 1943
Creator:
Abbott, Frank T., Jr.
System:
The UNT Digital Library
Interference effects of longitudinal flat plates on low-drag airfoils
Three airfoils were tested with an intersecting flat plate normal to the span as a preliminary study of interference effects on airfoils. Small interference effects were noted on the first two airfoils, while larger effects were noted on the NACA 66,2-422 section, which had previously been shown to be unconservative with respect to separation. Airfoils known to be conservative should be used for inboard sections subject to nacelle and fuselage interference.
Date:
November 1942
Creator:
Abbott, Ira H.
System:
The UNT Digital Library
Accelerations in fighter-airplane crashes
From Introduction: "This report describes some measurements of these quantities obtained by crashing fighter aircraft under circumstances approximating those observed in service."
Date:
November 4, 1957
Creator:
Acker, Loren W.; Black, Dugald O. & Moser, Jacob C.
System:
The UNT Digital Library
High-speed wind tunnels
Wind tunnel construction and design is discussed especially in relation to subsonic and supersonic speeds. Reynolds Numbers and the theory of compressible flows are also taken into consideration in designing new tunnels.
Date:
November 1936
Creator:
Ackeret, J.
System:
The UNT Digital Library
Aerodynamic Heat-Power Engine Operating on a Closed Cycle
"Hot-air engines with dynamic compressors and turbines offer new prospects of success through utilization of units of high efficiencies and through the employment of modern materials of great strength at high temperature. Particular consideration is given to an aerodynamic prime mover operating on a closed circuit and heated externally. Increase of the pressure level of the circulating air permits a great increase of limit load of the unit. This also affords a possibility of regulation for which the internal efficiency of the unit changes but slightly. The effect of pressure and temperature losses is investigated" (p. 1).
Date:
November 1942
Creator:
Ackeret, J. & Keller, D. C.
System:
The UNT Digital Library
Investigations on Wings With and Without Sweepback at High Subsonic Speeds
Drag tests at zero lift have been made at Mach numbers from 0.7 to approximately 0.95 in the high speed wind tunnel of the Institute of Aerodynamics, ETH, Zurich, on a group of untapered wings of aspect ratio 3.25, having sweep angles of 0 degree and 35 degrees. For each sweep angle, a series of geometrically similar models was tested at a constant Reynolds number to provide a verification of computed tunnel blocking corrections. Tests were also made for wings having thickness ratios of 0.09 and 0.12 and the results compared with results predicted by von Karman's similarity law.
Date:
November 1951
Creator:
Ackeret, Jakob; Degen, Max & Rott, Nikolaus
System:
The UNT Digital Library
Flying qualities of a high-performance personal-owner airplane
Report presenting an investigation to measure the flying qualities of a high-performance personal-owner airplane to investigate the possible causes of instrument flying accidents with that type of aircraft. Testing indicated that the lack of aerodynamic stall warning and rapid roll-off at the stall could contribute to stall-spin accidents with high-performance personal-owner aircraft. Results regarding the handling qualities and the control under instrument flying conditions are provided.
Date:
November 8, 1951
Creator:
Adams, James J. & Whitten, James B.
System:
The UNT Digital Library
A Comparison of Wing Loads Measured in Flight on a Fighter-Type Airplane by Strain-Gage and Pressure Distribution Methods
Note presenting pressure distribution measurements made on the wing of a fighter-type airplane to determine the span loading and to compare center-of-pressure results with those obtained by strain-gage measurements on the same airplane during a previous flight investigation. Flight tests were all made at a pressure altitude of about 30,000 feet and covered a Mach number range from approximately 0.35 to 0.81. Results regarding additional air load, spanwise center of pressure of additional air load, basic air load distribution, and span loading during a stall and buffeting are provided.
Date:
November 1949
Creator:
Aiken, William S., Jr. & Howard, Donald A.
System:
The UNT Digital Library
Flight Investigation to Determine the Aerodynamic Characteristics of Rocket-Powered Models Representative of a Fighter-Type Airplane Configuration Incorporating an Inverse-Taper Wing and a Vee Tail
From Summary: "Two rocket-powered models representative of a fighter-type airplane were investigated in flight at Mach numbers up to 1.01 and 1.07 by the Langley Pilotless Aircraft Research Division at its testing station at Wallops Island, Va. These models incorporated an inverse-taper wing and a vee tail and were flown with controls undeflected and wing and stabilizer set at 0 deg incidence. Values of lateral acceleration, normal acceleration velocity, and drag were obtained by use of telemeters and a Doppler velocimeter radar unit."
Date:
November 2, 1948
Creator:
Alexander, Sidney R.
System:
The UNT Digital Library
Estimation of the forces and moments acting on inclined bodies of revolution of high fineness ratio
Report presenting a discussion of the aerodynamic forces and moments on inclined bodies of revolution. An approximate theory to allow for the effects of viscosity is developed and applied. Results regarding the variation of lift and pitching moment, and center of gravity are provided.
Date:
November 14, 1949
Creator:
Allen, H. Julian
System:
The UNT Digital Library
The Knock-Limited Performance of Several Fuels Blended With S-2 Reference Fuel
Report discussing the results of testing conducted to determine the knock-limited performance of fuel blends containing 80 percent of S-2 reference fuel and 20 percent of several exploratory fuels. Butyl acetate, sec-butyl acetate, isopropyl acetate, sec-butyl alcohol, tert-butyl alcohol, isopropyl alcohol, cyclohexanol, methylcyclohexanol, isobutylcarbinol, sec-butylcarbinol, triethyl borate, and dimethylfuran were examined.
Date:
November 1944
Creator:
Alquist, Henry E.
System:
The UNT Digital Library
An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 1: Characteristics of a Wing Having a Double-Wedge Airfoil Section With Maximum Thickness at 20-Percent Chord
Report presenting an investigation of the low-speed characteristics of a 25-foot span triangular wing with an aspect ratio of 2. the airfoil section of the wing was a symmetrical double wedge with 5-percent maximum thickness at 20-percent chord. Results regarding the longitudinal characteristics, lateral characteristics, and directional characteristics are provided.
Date:
November 13, 1947
Creator:
Anderson, Adrien E.
System:
The UNT Digital Library
The aerodynamic characteristics of six commonly used Airfoils over a large range of positive and negative angles of attack
From Summary: "This paper presents the results of tests of six commonly used airfoils: the CYH, the N-22, the C-72, the Boeing 106, and the Gottingen 398. The lifts, drags, and pitching moments of the airfoils were measured through a large range of positive and negative angles of attack. The tests were made in the variable density wind tunnel of the National Advisory Committee for Aeronautics at a large Boeing 106, and the Gottingen 398 airfoils, the negative maximum lift coefficients were found to be approximately half the positive; but for the M-6 and the CYH, which have less effective values were, respectively, 0.8 and 0.6 of the positive values."
Date:
November 1931
Creator:
Anderson, Raymond F.
System:
The UNT Digital Library
The experimental and calculated characteristics of 22 tapered wings
From Summary: "The experimental and calculated aerodynamic characteristics of 22 tapered wings are compared, using tests made in the variable-density wind tunnel. The wings had aspect ratios from 6 to 12 and taper ratios from 1:6:1 and 5:1. The compared characteristics are the pitching moment, the aerodynamic-center position, the lift-curve slope, the maximum lift coefficient, and the curves of drag. The method of obtaining the calculated values is based on the use of wing theory and experimentally determined airfoil section data. In general, the experimental and calculated characteristics are in sufficiently good agreement that the method may be applied to many problems of airplane design."
Date:
November 17, 1937
Creator:
Anderson, Raymond F.
System:
The UNT Digital Library
Determination of Coupled and Uncoupled Modes and Frequencies of Natural Vibration of Swept and Unswept Wings From Uniform Cantilever Modes
Report presenting a solution for the coupled and uncoupled modes and frequencies of wings (swept or unswept) mounted on a fuselage. Characteristic equations describing symmetrical and antisymmetrical modes of vibrations are created and applied to various types of wing vibration in numerical examples.
Date:
November 1948
Creator:
Anderson, Roger A. & Houbolt, John C.
System:
The UNT Digital Library
Determination of Longitudinal Stability of the Bell X-1 Airplane From Transient Responses at Mach Numbers Up to 1.12 at Lift Coefficients of 0.3 and 0.6
Report presenting an analysis of a number of free-flight transient responses resulting from small stabilizer movements obtained during testing of the Bell X-1 airplane to obtain its longitudinal stability characteristics. A comparison of flight data and model test data is also provided.
Date:
November 7, 1950
Creator:
Angle, Ellwyn E. & Holleman, Euclid C.
System:
The UNT Digital Library
Flight and Wind-Tunnel Investigation to Determine the Aileron-Vibration Characteristics of 1/4-Scale Wing Panels of the Douglas D-558-2 Research Airplane
Report presenting a flight and wind-tunnel investigation to determine the aerodynamic vibration characteristics of ailerons for the Douglas D-558-2 airplane. Testing was conducted to investigate the possibilities of a single-degree-of-freedom flutter known as aileron "buzz" or aileron compressibility flutter. Results regarding the three types of aileron vibration observed and vibration amplitudes are provided.
Date:
November 30, 1948
Creator:
Angle, Ellwyn E. & Lundstrom, Reginald R.
System:
The UNT Digital Library
High-Speed Longitudinal-Stability and Control Characteristics of the Consolidated Vultee Lark Missile as Predicted from Wind-Tunnel Tests (TED No. NACA 2391)
"A high-speed wind-tunnel investigation of the aerodynamic characteristics of a full-scale model of the Consolidated Vultee Lark indicates that the missile possesses satisfactory longitudinal-stability and-control characteristics throughout the Mach number range from 0.2 to 0.85, but that the maximum lift coefficients developed are not high enough to insure interception of the target at high altitudes. A reduction in wing loading appears advisable. Although the static longitudinal stability at zero angle of attack changes with Mach number and with lift coefficient, satisfactory control should be possible at all times as the tails retain their relatively large effectiveness throughout the range of Mach numbers and lift coefficients tested" (p. 1).
Date:
November 19, 1946
Creator:
Axelson, John A. & Martin, Andrew
System:
The UNT Digital Library
Numerical Evaluation of the Wake-Survey Equations for Subsonic Flow Including the Effect of Energy Addition
Report presenting direct-reading tables and charts for determining the drag or thrust coefficients from wake-survey measurements in the subsonic speed range. Additionally, numerical examples are provided using information from the tables.
Date:
November 1945
Creator:
Baals, Donald D. & Mourhess, Mary J.
System:
The UNT Digital Library
Variable Pitch Propellers
In this report are described four different types of propellers which appeared at widely separated dates, but which were exhibited together at the last Salon de l'Aeronautique. The four propellers are the Chaviere variable pitch propeller, the variable pitch propeller used on the Clement Bayard dirigible, the variable pitch propeller used on Italian dirigibles, and the Levasseur variable pitch propeller.
Date:
November 1920
Creator:
Bacon, D. L.
System:
The UNT Digital Library
The "Universal" Adjustable and Reversible Propeller Built by Paragon Engineers, Inc., Baltimore, MD
"A device which does for the aircraft what change speed gears do for the automobile is the invention of Spencer Heath. It comprises a system of special blades and a mechanism for varying the pitch of the blades from zero to 360 degrees, while in flight or otherwise. By adjusting the pitch, either before starting or while the engine is running, to a less than normal angle, the engine is allowed to pick up speed and deliver its maximum power which is necessary in taking-off with a heavier load than the same airplane could otherwise normally carry" (p. 1).
Date:
November 1922
Creator:
Bacon, David L.
System:
The UNT Digital Library
Evaporation and Spreading of Isooctane Sprays in High Velocity Air Streams
Memorandum presenting an investigation of the evaporation and spreading of isooctane sprays over a range of inlet-air conditions common in ram-jet engines. The total and liquid fuel distribution across the duct were determined. Over the specified ranges in the investigation, expressions were obtained which related the evaporation rate and degree of spreading of the sprays to the experimental variables.
Date:
November 16, 1953
Creator:
Bahr, Donald W.
System:
The UNT Digital Library
Some Measurements of Buffeting Encountered by Douglas D-558-II Research Airplane in the Mach Number Range From 0.5 to 0.95
Report presenting a flight investigation of the variation of the intensity of buffeting with lift and Mach number using a Douglas D-558-II research airplane over a range of Mach numbers and altitudes. Buffeting was encountered during flight at all Mach numbers attained and during level flight at Mach numbers above 0.9. Results regarding the relationship between lift, angle of attack, and buffeting, buffet frequencies, and intensity of buffeting are provided.
Date:
November 20, 1953
Creator:
Baker, Thomas F.
System:
The UNT Digital Library
Flight data pertinent to buffeting and maximum normal-force coefficient of the Douglas X-3 research airplane
Report presenting the X-3 airplane, which has a straight 4.5-percent-thick wing of modified hexagonal section, which has been flown to maximum wing normal-force coefficients in the Mach number range from 0.7 to 1.1 at an average altitude of 30,000 feet. Measurements were made of airplane and wing-panel maximum normal-force coefficients and of some buffeting characteristics.
Date:
November 20, 1957
Creator:
Baker, Thomas F.; Martin, James A. & Scott, Betty J.
System:
The UNT Digital Library