Serial/Series Title
Country
States
439 Matching Results
Results open in a new window/tab.
Rocket-Model Investigation of the Longitudinal Stability, Drag, and Duct Performance of a 60 Degree Delta-Wing Canard Aircraft With Twin Side Inlets at Mach Numbers From 0.80 to 1.70
Report discussing a flight test on a rocket-boosted canard aircraft with 60 degree delta lifting surfaces, twin normal-shock-type side inlets, and twin vertical tails. The drag, longitudinal stability, and duct performance data were obtained for a range of Mach and Reynolds numbers.
Date:
March 29, 1954
Creator:
Bond, Aleck C. & Swanson, Andrew G.
System:
The UNT Digital Library
Flight Test of an End-Burning Solid-Fuel Ramjet
Report presenting a flight investigation of a rocket-launched ram-jet engine incorporating an end-burning solid fuel. Results regarding acceleration, altitude, booster separation, survival time of booster adapter, and air specific impulse are provided.
Date:
March 25, 1954
Creator:
Bartlett, Walter A., Jr.
System:
The UNT Digital Library
Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depressions on a 30-Degree Blunted Nose Cone
Report discussing heat data obtained on concave and convex hemispherical nose shapes and hemispherical depressions on a blunted 30-degree nose cone at a variety of Mach numbers. Both hot-jet tests and flight tests were carried out.
Date:
March 10, 1958
Creator:
Hopko, Russell N. & Strass, H. Kurt
System:
The UNT Digital Library
Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 1/20-Scale Model of the McDonnell F4H-1 Airplane at Mach Numbers of 1.59, 1.89, and 2.09
Report discussing testing on the drag, longitudinal stability, and lateral stability characteristics of a model of the McDonnell F4H-1 airplane. The minimum drag coefficients, neutral point, horizontal-tail-incidence range, static directional stability, and effective dihedrals are presented.
Date:
March 23, 1956
Creator:
Carmel, Melvin M. & Gregory, Donald T.
System:
The UNT Digital Library
Total-Pressure-Recovery Characteristics of a Model of the McDonnell XF3H-1 Inlets and Forebody in a Free Jet at a Mach Number of 1.55
Report presenting free jet tests of a model of the inlets and forebody of the McDonnell XF3H-1 airplane with the original and two alternate nose shapes. Results regarding the total-pressure recovery after diffusion, maximum mass-flow ratio, inlet total-pressure profile, shadowgraphs, flow variation, and pressure oscillations are provided.
Date:
March 12, 1952
Creator:
Merlet, Charles F. & Carter, Howard S.
System:
The UNT Digital Library
Aerodynamic Measurements Made During Navy Investigation of Human Tolerance to Wind Blasts
From Summary: "This report presents the aerodynamic measurements made during a Navy investigation conducted in the Langley 8-foot high speed tunnel to determine the actual human tolerance to wind blasts."
Date:
March 11, 1947
Creator:
Loving, Donald L.
System:
The UNT Digital Library
Longitudinal Stability and Control Characteristics of a Semispan Airplane Model With a Swept-Back Tail From Tests at Transonic Speeds by the NACA Wing-Flow Method
Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics of a semispan airplane model with a wing of conventional plan form and a horizontal tail swept back 45 degrees at transonic speeds. Measurements were made of lift and angle of attack for trim at several stabilizer and elevator settings.
Date:
March 28, 1947
Creator:
Zalovcik, John A. & Sawyer, Richard H.
System:
The UNT Digital Library
Two-dimensional wind-tunnel investigation at high Reynolds numbers of two symmetrical circular-arc airfoil sections with high-lift devices
Report presenting an investigation of two symmetrical circular-arc airfoils of 6 and 10 percent thickness equipped with leading-edge and trailing-edge high-lift devices. A trialing-edge flap, drooped-nose flap, and leading-edge extensible flap were all tested. Results regarding the plain airfoils, airfoils with high-lift devices, combined deflection of high-lift devices, and low-drag-control flaps are provided.
Date:
March 12, 1947
Creator:
Underwood, William J. & Nuber, Robert J.
System:
The UNT Digital Library
Drag Measurements of Symmetrical Circular-Arc and NACA 65-009 Rectangular Airfoils Having an Aspect Ratio of 2.7 as Determined by Flight Tests at Supersonic Speeds
Report discussing testing to determine the drag characteristics at zero lift of a wing with a circular-arc airfoil section with a maximum thickness of 9 percent chord. The results were compared to previous testing on an NACA 65-009 airfoil. It was found that the NACA airfoil had lower drag coefficients than the circular-arc airfoil tested in this experiment.
Date:
March 7, 1947
Creator:
Alexander, Sidney R.
System:
The UNT Digital Library
Results of preliminary flight investigation of aerodynamic characteristics of the NACA two-stage supersonic research model RM-1 stabilized in roll at transonic and supersonic velocities
Report presenting the design of a two-stage, solid-fuel, rocket-propelled, general research pilotless aircraft suitable for investigating stability and control at supersonic velocities. The flight test investigation is described and information is provided for zero-length launchers and operational flight-test techniques of two-stage rockets. Results regarding launching characteristics and lateral stabilization and control flight tests are provided.
Date:
March 19, 1947
Creator:
Pitkin, Marvin; Garner, William N. & Curfman, Howard J., Jr.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Wing Inlets for a Four-Engine Airplane
Report presenting an investigation in the propeller-research tunnel to develop wing-leading-edge inlets for locations between the inboard and outboard nacelles on each wing of a four-engine airplane. Testing was performed on the basic wing and original inlet as well as NACA-developed inlets for two versions of the airplane.
Date:
March 11, 1947
Creator:
Bartlett, Walter A., Jr. & Goral, Edwin B.
System:
The UNT Digital Library
Initial Flight Tests of the NACA FR-2, a High-Velocity Rocket-Propelled Vehicle for Transonic Flutter Research
Report presenting initial flight tests of two simplified flutter vehicles. Test results were in agreement with the results of the freely-falling-body test in that the wing failures in the transonic range occurred at velocities greater than the flutter velocity calculated from the two-dimensional theory.
Date:
March 4, 1948
Creator:
Barmby, J. G. & Teitelbaum, J. M.
System:
The UNT Digital Library
Pressure Distributions on the Blade Sections of the NACA 10-(3)(090)-03 Propeller Under Operating Conditions
The third report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(090)-03 propeller.
Date:
March 22, 1950
Creator:
Johnson, Peter J.
System:
The UNT Digital Library
Exploratory Investigation of Leading-Edge Chord-Extensions to Improve the Longitudinal Stability Characteristics of Two 52 Degree Sweptback Wings
Report presenting exploratory testing obtained with leading-edge wing chord-extensions on two 52 degree sweptback wings. The wings had the same aspect ratio but different airfoil sections. Results regarding force characteristics and flow characteristics are provided.
Date:
March 10, 1950
Creator:
Furlong, G. Chester
System:
The UNT Digital Library
Performance of High-Pressure-Ratio Axial-Flow Compressor Using Highly Cambered Naca 65-Series Blower Blades at High Mach Numbers
"A complete stage of an axial-flow compressor was designed and built to investigate the possibility of obtaining a high pressure ratio with an acceptable efficiency through the use of the optimum combination of high blade loading and high relative inlet Mach number. Over-all stage performance was investigated over a range of flows at equivalent tip speeds of 418 to 836 feet per second. At design speed (836 ft/sec), a peak total-pressure ration of 1.445 was obtained with an adiabatic efficiency of 0.89. For design angle of attack at the mean radius, a total-pressure ratio of 1.392 was obtained" (p. 1).
Date:
March 28, 1950
Creator:
Voit, Charles H.; Guentert, Donald C. & Dugan, James F.
System:
The UNT Digital Library
Experimental investigation of the effectiveness of various suction-slot arrangements as a means for increasing the maximum lift of the NACA 65(sub 3)-018 airfoil section
Report presenting a wind-tunnel investigation to explore the possibility of employing boundary-layer suction slots as a means for delaying laminar separation at the leading edge and turbulent separation over the rear portions of the airfoil section at high lift coefficients. Results regarding lift and drag are explored.
Date:
March 31, 1950
Creator:
Racisz, Stanley F.
System:
The UNT Digital Library
Further Investigation of a Gas Turbine with National Bureau of Standards Body 4811C Ceramic Rotor Blades
Memorandum presenting an investigation of 4811C ceramic blades and the problems involved in the adaption of ceramic materials to stressed turbine components. Results regarding spin tests and rotating heat-shock runs are provided.
Date:
March 9, 1950
Creator:
Freche, John C.
System:
The UNT Digital Library
Preliminary Investigation of a Submerged Air Scoop Utilizing Boundary-Layer Suction to Obtain Increased Pressure Recovery
Report presenting an investigation of a submerged air scoop consisting of a conventional scoop located in a dimple in the fuselage surface at low speeds. Results regarding a study of the basic inlet without suction, a comparison of arrangements using boundary-layer control, the performances of the most desirable configurations with a certain boundary layer, and variation of boundary-layer thickness are provided.
Date:
March 17, 1950
Creator:
Nichols, Mark R. & Pierpont, P. Kenneth
System:
The UNT Digital Library
Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic bump method
Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Date:
March 2, 1950
Creator:
Vogler, Raymond D.
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and NACA 65A004 airfoil section: transonic-bump method
From Introduction: "This paper presents the results of an investigation of force and moment characteristics for a wing with an unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and an NACA 65A004 airfoil section parallel to the free stream."
Date:
March 8, 1950
Creator:
Polhamus, Edward C. & Campbell, George S.
System:
The UNT Digital Library
An analysis of the forces and pressure distribution on a wing with the leading edge swept back 37.25 degrees
Report presenting testing of a semispan model of a wing with the leading edge swept back 37.25 degrees, an aspect ratio of 6.04, and a taper ratio of 0.5 in order to ascertain the compressibility effects on the forces, moments, and surface pressures. Lift, drag, and pitching-moment data along with chordwise distribution of static pressure at five spanwise stations are presented for a range of Mach numbers and a constant Reynolds number. Results regarding force and moment characteristics, critical flow and drag increase at high subsonic Mach numbers, and pressure changes with increasing Mach number are provided.
Date:
March 30, 1950
Creator:
Edwards, George G. & Boltz, Frederick W.
System:
The UNT Digital Library
Cooling of ram jets and tail-pipe burners: analytical method for determining temperatures of combustion chamber having annular cooling passage
Report presenting an analytical method for calculating the maximum wall temperature of a tail-pipe burner or a ramjet combustion chamber cooled by air or gas flowing through a surrounding annular passage.
Date:
March 21, 1950
Creator:
Koffel, William K.; Stamper, Eugene & Sanders, Newell D.
System:
The UNT Digital Library
Two-Dimensional Wind-Tunnel Investigation of Two NACA 7-Series Type Airfoils Equipped With a Slot-Lip Aileron, Trailing-Edge Frise Aileron, and a Double Slotted Flap
Report presenting a wind-tunnel investigation of two NACA 7-series type airfoils, one with 17.7-percent chord thickness and one with 15.4-percent chord thickness, each quipped with a 30-percent-airfoil-chord double slotted flap, a slot-lip aileron, and a trailing-edge Frise aileron with two amounts of overhang balance. Measurements of airfoil lift and drag, Frise aileron hinge moment, and slot-lip aileron hinge moment were obtained through a large range of deflection of flap, Frise aileron, and slot-lip aileron and section angle of attack. Satisfactory lateral control can be obtained by using this combination of airfoils, flaps, and ailerons.
Date:
March 28, 1949
Creator:
Braslow, Albert L. & Visconti, Fioravante
System:
The UNT Digital Library
Drag of a Wing-Body Configuration Consisting of a Swept-Forward Tapered Wing Mounted on a Body of Fineness Ratio 12 Measured During Free Fall at Transonic Speeds
Report discussing an investigation to determine the drag of a configuration with a body of fitness ratio 12 with stabilizing tail surfaces and a 12-percent-thick 30-degree swept-forward wing using the free-fall method. The drag oft he wing and the total drag were measured separately and compared. The swept-forward wing was found to greatly increase the effect of drag on the body-tail combination.
Date:
March 13, 1947
Creator:
Thompson, Jim Rogers & Mathews, Charles W.
System:
The UNT Digital Library