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An analysis of the normal accelerations and airspeeds of a four-engine airplane type in postwar commercial transport operations on trans-Pacific and Caribbean-South American routes
Report presenting an analysis of normal-acceleration and airspeed data on several transport airplanes of a four-engine type during postwar commerical operations on trans-Pacific and Caribbean-South American routes of the same airlines. The results indicate that the acceleration increment corresponding to the limit-gust-load-factor increment may be exceed about twice in all of the flight miles for each route. Results regarding accelerations, flight loads, gust encounters, and speeds are provided.
Date:
August 1950
Creator:
Coleman, Thomas L. & Schumacher, Paul W. J.
System:
The UNT Digital Library
Calculated Engine Performance and Airplane Range for Variety of Turbine-Propeller Engines
Note presenting an analysis of the performance of basic, reheat, regenerative, and regenerative-plus-reheat turbine-propeller engines. The analysis covered an overall range of flight speeds, altitudes, and turbine-inlet temperatures for a range of compressor pressure ratios.
Date:
August 1950
Creator:
Nagey, Tibor F. & Martin, Cecil G.
System:
The UNT Digital Library
Charts for Estimating Downwash Behind Rectangular, Trapezoidal, and Triangular Wings at Supersonic Speeds
Note presenting charts for estimating the downwash behind wings in a supersonic stream. The wing plan forms for which compositions are made include rectangular wings with reduced aspect ratios of 2, 4, 8, and 12; trapezoidal wings with reduced aspect ratios ranging from 2 to 12.8 and taper ratios of 1/2 and 1/4; and triangular wings with reduced aspect ratios of 8 and 12. A procedure is indicated to correct for the displacement and the distortion of the trailing vortex sheet.
Date:
August 1950
Creator:
Haefeli, Rudolph C.; Mirels, Harold & Cummings, John L.
System:
The UNT Digital Library
Comparison of the Experimental Pressure Distribution on an NACA 0012 Profile at High Speeds With That Calculated by the Relaxation Method
Note presenting pressure-distribution measurements made on a 5-inch-chord NACA 0012 airfoil at zero angle of attack in the Langley rectangular high-speed tunnel, a 4- by 18-inch closed-throat tunnel, and compared with results calculated by Emmons for an equivalent airfoil-channel configuration by using the relaxation method.
Date:
August 1950
Creator:
Amick, James L.
System:
The UNT Digital Library
Contribution to the Problem of Buckling of Orthotropic Plates, With Special Reference to Plywood
Planar stress-strain relations and bending stress-strain relations are presented for elastic orthotropic plates and specialized to plywood. These relations are used to derive the differential equation and energy expression for the buckling of orthotropic rectangular plates whose principal stiffness directions are not parallel to the plate edges. Buckling analyses are made for the case of pure compression and pure shear of a long plate-strip.
Date:
August 1950
Creator:
Thielemann, Wilhelm
System:
The UNT Digital Library
Critical stress of plate columns
Report presenting solutions for the elastic buckling stress of flat rectangular plates with simply supported or fixed ends when loaded as columns. The procedure for determining the critical stress of plate columns with intermediate end fixities is also given.
Date:
August 1950
Creator:
Houbolt, John C. & Stowell, Elbridge Z.
System:
The UNT Digital Library
Density fields around a sphere at Mach numbers 1.30 and 1.62
From Summary: "Interferograms were taken of the flow around a sphere at Mach numbers of 1.30 and 1.62. The results of the evaluation of these interferograms are shown as plots of contours of constant density ratio in the flow field around the sphere and as the distribution of flow variables along the axis of symmetry between the shock wave and the sphere. In appendixes the theory of the analysis is reviewed, sources of error are discussed, and the detailed procedure used in the evaluation of interferograms is described."
Date:
August 1950
Creator:
Gooderum, Paul B. & Wood, George P.
System:
The UNT Digital Library
Dependence of the Elastic Strain Coefficient of Copper on the Pre-Treatment
The effect of various pre-treatments on the elastic strain coefficient (alpha) (defined as the reciprocal of the modulus of elasticity E) (Epsilon) and on the mechanical hysteresis of copper has been investigated. Variables comprising the pre-treatments were pre-straining by stretching in a tensile testing machine and by drawing through a die, aging at room and elevated temperatures and annealing. The variation of the elastic strain coefficient with test stress was also investigated.
Date:
August 1950
Creator:
Kuntze, Wilhelm
System:
The UNT Digital Library
Effect of an unswept wing on the contribution of unswept-tail configuration to the low-speed static and rolling-stability derivatives of a midwing airplane model
Report presenting an investigation conducted in the stability tunnel to determine the effect of an unswept wing on the contribution of unswept-tail configurations to the low-speed-static- and rolling-stability derivatives of a midwing airplane model. The results show that there tend to be only small differences in the tail contributions to the static-lateral-stability derivatives for configurations with the wing on and wing off.
Date:
August 1950
Creator:
Letko, William & Riley, Donald R.
System:
The UNT Digital Library
Effect of chemical reactivity of lubricant additives on friction and surface welding at high sliding velocities
Report presenting an investigation of the effect of chemical reactivity of lubricant additives on friction at high sliding velocities. The investigation was conducted with a kinetic-friction apparatus consisting of an elastically restrained spherical rider specimen sliding on a rotating steel disk lubricated with cetane containing lubricant additives of different chemical reactivities. Results regarding chlorine compounds and sulfur compounds are provided.
Date:
August 1950
Creator:
Bisson, Edmond E.; Swikert, Max A. & Johnson, Robert L.
System:
The UNT Digital Library
Effect of heat and power extraction on turbojet-engine performance 2: effect of compressor-outlet air bleed for specific modes of engine operation
Report presenting the calculation of the effect of air bleed from the compressor outlet on the performance of turbojet engines with variable-area and rated-area tail-pipe nozzles using generalized performance charts. The effect of altitude, compressor-inlet temperature, and flight Mach number on engine performance with air bleed are provided.
Date:
August 1950
Creator:
Rom, Frank E. & Koutz, Stanley L.
System:
The UNT Digital Library
Effect of Initial Mixture Temperature on Flame Speeds and Blow-Off Limits of Propane - Air Flames
Report presenting the effect of initial mixture temperature on flame speeds in the laminar flow region and on blow off limits in both laminar and turbulent-flow regions was investigated for Bunsen type flames of propane and air. Flame speeds were determined at various mixture compositions at a range of temperatures and by measuring the area of the Bunsen cone from shadowgraphs.
Date:
August 1950
Creator:
Dugger, Gordon L.
System:
The UNT Digital Library
Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 2: Rotor Blades With 15 Fins in Cooling-Air Passages
Report presenting an investigation to experimentally determine the effectiveness of air-cooling several configurations of turbine blades in a turbojet engine. The results of the second blade configuration, which consists of a hollow blade shell with 15 fins inserted, are provided. The factors involved in the design of the blade configuration are also included.
Date:
August 1950
Creator:
Hickel, Robert O. & Ellerbrock, Herman H., Jr.
System:
The UNT Digital Library
Experimental investigation of the effect of vertical-tail size and length of fuselage shape and length on the static lateral stability characteristics of a model with 45 degree sweptback wing and tail surfaces
Report presenting an investigation to determine the effects of vertical-tail size and length and of fuselage shape and length on the lateral static stability characteristics of a model with a wing and vertical tails with the quarter-chord line swept back 45 degrees. Results indicated that the directional instability of the fuselage was about two-thirds as large as that predicted by classical theory. Results regarding wing characteristics, fuselage characteristics, vertical-tail effectiveness, and interference effects are provided.
Date:
August 1950
Creator:
Queijo, M. J. & Wolhart, Walter D.
System:
The UNT Digital Library
Flight investigation of the effect of transient wing response on measured accelerations of a modern transport airplane in rough air
Report presenting a flight investigation on a transport airplane to determine the effect of transient wing response in rough air on acceleration measurements at the center of gravity of the airplane. Flights were made in clear-air turbulence over a range of altitudes for two speed conditions and different wing weights. Results indicate that the peak recorded center-of-gravity acceleration increments were over 20 percent higher than the true airplane acceleration increments.
Date:
August 1950
Creator:
Shufflebarger, C. C. & Mickleboro, Harry C.
System:
The UNT Digital Library
A General Integral Form of the Boundary-Layer Equation for Incompressible Flow With an Application to the Calculation of the Separation Point of Turbulent Boundary Layers
Note presenting a general integral form of the boundary-layer equation that is derived from the Prandtl partial-differential boundary-layer equation. The general integral equation, valid for either laminar or turbulent incompressible boundary-layer flow, contains the Von Karman momentum equation, the kinetic-energy equation, and the Loitsianskii equation as special cases.
Date:
August 1950
Creator:
Tetervin, Neal & Lin, Chia Chiao
System:
The UNT Digital Library
Investigation of Boundary-layer Control to Improve the Lift and Drag Characteristics of the NACA 65â‚‚-415 Airfoil Section with Double Slotted and Plain Flaps
From summary: "A two-dimensional wind-tunnel investigation has been made of the relative effectiveness of two methods of boundary-layer control in increasing the maximum lift coefficient of an NACA 652-415 airfoil section."
Date:
August 1950
Creator:
Horton, Elmer A.; Racisz, Stanley Frank & Paradiso, Nicholas J.
System:
The UNT Digital Library
Investigation of properties of AISI type 310B alloy sheet at high temperatures
Report presenting an investigation of an alloy with a composition of 25 percent chromium, 20 percent nickel, and 2 percent silicon (AISI Type 310B alloy), which is known to be subject to low ductility in the temperature range of 1200 to 1400 degrees F. The primary investigation involved tensile tests at 1700 and 1800 degrees in order to determine if that would cause further loss of ductility, resulting in brittleness at lower temperatures. Results regarding the tensile properties, rupture properties, and a microstructural examination are provided.
Date:
August 1950
Creator:
Reynolds, E. E.; Freeman, James W. & White, Albert Easton
System:
The UNT Digital Library
Investigations of Lateral Stability of a Glide Bomb Using Automatic Control Having No Time Lag
The investigation of the lateral stability of an automatically controlled glide bomb led also to the attempt of clarifying the influence of a phugoid oscillation or of any general longitudinal oscillation on the lateral stability of a glide bomb. Under the assumption that its period of oscillation considerably exceeds the rolling and yawing oscillation and that c(sub a) is, at least in sections, practically constant, the result of this test is quite simple. It becomes clear that the influence of the phugoid oscillation may be replaced by suitable variation of the rolling-yawing moment on a rectilinear flight path instead of the phugoid oscillation.
Date:
August 1950
Creator:
Sponder, E. W.
System:
The UNT Digital Library
Laminar-boundary-layer heat-transfer characteristics of a body with a pressure gradient at supersonic speeds
Report presenting local rates of heat transfer over the negative pressure-gradient region of a pointed body of revolution with a fineness ratio of 6:1, a vertex angle of 37 degrees, and a contour generated by rotating a segment of a parabola.
Date:
August 1950
Creator:
Wimbrow, William R. & Scherrer, Richard
System:
The UNT Digital Library
Lift-Cancellation Technique in Linearized Supersonic-Wing Theory
Note presenting a lift-cancellation technique for determining load distributions on thin wings at supersonic speeds. A general expression is derived for the load distribution over a cancellation wing. The lift cancellation technique is illustrated for swept wings with curvilinear plan forms.
Date:
August 1950
Creator:
Mirels, Harold
System:
The UNT Digital Library
Low-speed characteristics of four cambered, 10-percent-thick NACA airfoil sections
Report presenting a two-dimensional low-speed investigation of four thin, cambered airfoil sections. The data included measurements of lift, drag, pitching moment, and chordwise distribution of pressure. The maximum lift section coefficients, stall, effect of Reynolds number on maximum lift, surface roughness, and increment of maximum lift by a simulated split flap are described in detail.
Date:
August 1950
Creator:
McCullough, George B. & Haire, William M.
System:
The UNT Digital Library
Low-Speed Investigation of the Stalling of a Thin, Faired, Double-Wedge Airfoil with Nose Flap
Note presenting an investigation of the stalling characteristics of a 4.23-percent-thick, faired, double-wedge airfoil section with and without a plain nose flap. Flap chord equal to 12, 16, 20, and 25 percent of the airfoil chord were tested.
Date:
August 1950
Creator:
Rose, Leonard M. & Altman, John M.
System:
The UNT Digital Library
Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low-Speed Wind Tunnel as Affected by the Tunnel Walls
Note presenting an investigation conducted to determine the efficacy of simulating the flow over a swept wing of infinite span by mounting a swept wing across the test section of a closed rectangular wind tunnel. Equations are presented from which the upwash velocities induced by the tunnel walls were calculated for the swept wing. Results regarding pressure distribution, force and moment characteristics, and air flow over the swept wing are provided.
Date:
August 1950
Creator:
Dannenberg, Robert E.
System:
The UNT Digital Library