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Effect of Chordwise Vanes on Amplitude of Tail Buffeting
"Flight tests have been made with a P-51D airplane to determine the effect of chordwise vanes on the amplitude of tail buffeting. The tests made during abrupt pull-ups to the buffeting boundary included strain measurements on wing and tail and tuft studies over the wing. The results indicate that the vanes tested have no appreciable effect on the amplitude of tail buffeting" (p. 1).
Date:
November 10, 1947
Creator:
Stokke, Allen R.
System:
The UNT Digital Library
Preliminary Investigation of Effects of Alpha-Particle Bombardment on the Creep Rate of Aluminum
Memorandum presenting a preliminary investigation to determine the effects of alpha-particle bombardment on the creep rate of aluminum wire at 400 degrees Fahrenheit. The alpha radiation from an 85-millicurie polonium source appeared to decrease slightly the creep rate of the aluminum.
Date:
July 3, 1947
Creator:
Kittel, J. Howard
System:
The UNT Digital Library
An investigation of the effect of tip shape on the low-speed aerodynamic characteristics of large-scale swept wings
Report presenting an investigation of the effect of tip shape on the aerodynamic characteristics of large-scale 45 degrees swept-forward and 45 degrees swept-back wings. The results show that none of the variations of tip shape investigated nor the addition of bodies of revolution at the tips produced major changes in the characteristics of the swept wings.
Date:
November 13, 1947
Creator:
Walling, Walter C.
System:
The UNT Digital Library
Characteristics of a 15-Percent-Chord and a 35-Percent-Chord Plain Flap on the NACA 0006 Airfoil Section at High Subsonic Speeds
Memorandum presenting wind-tunnel tests to determine the aerodynamic characteristics of a 15-percent- and a 35-percent-chord plain trailing-edge flap on the NACA 0006 airfoil section. Simultaneous measurements of section lift, drag, and pitching moment were made over a range of Mach numbers, angles of attack, and flap deflections.
Date:
October 2, 1947
Creator:
Ilk, Richard J.
System:
The UNT Digital Library
Preliminary Investigation of a Ceramic Lining for a Combustion Chamber for Gas-Turbine Use
Combustion chamber liners for gas turbines and experimental set-ups were tested for failure. A ceramic-lined test chamber was operated at fuel/air ratios up to 0.050. Thermal-shock evaluation indicated that a ceramic lining, which expands after firing, would crack but would not fall apart during operation. Refractoriness of the lining and the resistance to mechanical shock were adequate. In general, shell temperature reductions of approximately 400 deg F were effected by the use of this lining at fuel/air ratios of 0.016 and 0.050. The mechanism of failure of the ceramic lining was induced by sudden heating and cooling during operation.
Date:
April 12, 1948
Creator:
Woodward, William H. & Bobrowsky, A. R.
System:
The UNT Digital Library
Wind-tunnel development of optimum double-slotted-flap configurations for seven thin NACA airfoil sections
Report presenting an investigation in the two-dimensional low-turbulence tunnels to develop optimum double-slotted-flap configurations for seven thin NACA airfoil sections. Each was equipped with the same flaps and measured at the same Reynolds numbers. Results regarding the lift characteristics and pitching moment are provided.
Date:
April 28, 1947
Creator:
Cahill, Jones F. & Racisz, Stanley F.
System:
The UNT Digital Library
Preliminary investigation of hydrazine as a rocket fuel
Report presenting an investigation of the properties of hydrazine, stability and corrosiveness with a number of construction materials, sensitivity to detonation and temperature, and spontaneous reaction with the oxidants, concentrated hydrogen peroxide, sodium permanganate solution, fuming nitric acid, and tetranitromethane. Results regarding corrosion and stability, sensitivity to temperature and detonation, and theoretical calculations are provided.
Date:
May 24, 1948
Creator:
Ordin, Paul M.; Miller, Riley O. & Diehl, John M.
System:
The UNT Digital Library
Results of flight tests at supersonic speeds to determine the effect of body nose fineness ratio on body and wing drag
Report presenting flight tests of rocket-powered models at supersonic speeds to determine the effect of nose fineness ratio of winged bodies on total and component drag at high Mach numbers. Wingless models of three nose fineness ratios and winged models of two nose fineness ratios flown through a range of Mach numbers. Results regarding total drag, body drag, and wing drag are provided.
Date:
June 26, 1947
Creator:
Katz, Ellis R.
System:
The UNT Digital Library
Preliminary investigation of spoiler lateral control on a 42 degree sweptback wing at transonic speeds
Investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the rolling-effectiveness characteristics of a spoiler on a double-wedge-type semispan wing with a sweepback angle of 42 degrees. Results regarding the variation of rolling-moment coefficient, spoiler effectiveness, and rolling effectiveness are provided.
Date:
August 12, 1947
Creator:
Schneiter, Leslie E. & Ziff, Howard L.
System:
The UNT Digital Library
Static tests of a shrouded and an unshrouded propeller
Report presenting outdoor static testing made on two high-solidity propellers of different design, one shrouded and the other unshrouded. Three shrouds were tested to determine the effects of shroud length and exit area. Results regarding the action of shroud, results and comparison of propellers, and comparison with theory are provided.
Date:
February 9, 1948
Creator:
Platt, Robert J., Jr.
System:
The UNT Digital Library
Subsonic flight investigation of rectangular ram jet over range of altitudes
Report presenting a flight investigation conducted on a rectangular ramjet incorporating a V-shaped gutter-type flame holder over a range of fuel air ratios, combustion chamber inlet velocities, and pressure altitudes.
Date:
January 19, 1948
Creator:
Messing, Wesley E. & Black, Dugald O.
System:
The UNT Digital Library
Full-Scale Investigation of the Maximum Lift and Flow Characteristics of an Airplane Having Approximately Triangular Plan Form
Report discussing an investigation of the DM-1 glider, which has an approximately triangular plan form, with auxiliary studies of a model of triangular wings. The pitching-moment coefficient, drag coefficient, and angle of attack with the lift coefficient are provided. Results indicated that the angles of descent without power are likely to be prohibitive and airplanes with the tested type of wings will not be able to land safely without power.
Date:
February 12, 1947
Creator:
Wilson, Herbert A., Jr. & Lovell, J. Calvin
System:
The UNT Digital Library
Comparative Drag Measurements at Transonic Speeds of 6-Percent-Thick Airfoils of Symmetrical Double-Wedge and Circular-Arc Sections From Tests by the NACA Wing-Flow Method
Report presenting comparative drag measurements at zero lift at transonic speeds for two sharp-leading-edge airfoils using the NACA wing-flow method. One airfoil had a symmetrical circular-arc section and one had a symmetrical double-wedge section. The primary difference in the drag characteristics of the two airfoils at zero lift is the earlier drag rise of the double-wedge section.
Date:
April 8, 1947
Creator:
Silsby, Norman S.
System:
The UNT Digital Library
Estimate of Hull-Weight Change with Varying Length-Beam Ratio for Flying Boats
"A study has been made of the variation of seaplane hull weight with length-beam ratio in a systematic series of hulls designed for constant gross weight and similar spray characteristics. It is found that increases in the length-beam ratio bring about small reductions in the hull weight if it is assumed that seaplanes having the same weight and bottom shape will be designed for the same load factor. A short discussion is also given to show the reduction in load factor that may occur with high length-beam ratios" (p. 1).
Date:
August 14, 1947
Creator:
Benscoter, Stanley U.
System:
The UNT Digital Library
Flight Investigation to Determine the Hinge Moments of a Beveled-Edge Aileron on a 45 Degree Sweptback Wing at Transonic and Low Supersonic Speeds
Report discussing testing of a model of the pilotless aircraft RM-1 to measure aileron hinge moments in flight in order to determine the reason for loss of roll stabilization at supercritical speeds in flight. The aileron was found to become quickly underbalanced over the full deflection range at supercritical speeds. Information about the general flight behavior, aileron hinge moments, and roll stabilization of the model is provided.
Date:
November 12, 1947
Creator:
Gardner, William N. & Curfman, Howard J., Jr.
System:
The UNT Digital Library
An approximate method for calculating the effect of surface roughness on the drag of an airplane
From Summary: "A method for computing the effect of surface roughness on the drag coefficient of an airplane is presented. Calculated results using this method are compared with experimental results from both flight and wind-tunnel tests. In general, the agreement is believed satisfactory."
Date:
July 23, 1947
Creator:
Hall, Charles F. & Fitzgerald, Fred F.
System:
The UNT Digital Library
An Investigation of Convergent-Divergent Diffusers at Mach Number 1.85
An investigation has been conducted in the Cleveland 18- by 18-inch supersonic tunnel at a Mach number of 1.85 and angles of attack from 0 deg to 5 deg to determine optimum design configurations for a convergent-divergent type of supersonic diffuser with a subsonic diffuser of 5 deg included divergence angle. Total pressure recoveries in excess of theoretical recovery across a normal shock at a free-stream Mach number of 1.85 wore obtained with several configurations.
Date:
April 28, 1947
Creator:
Wyatt, DeMarquis D. & Hunczak, Henry R.
System:
The UNT Digital Library
Initial Test in the Transonic Range of Four Flutter Airfoils Attached to a Freely Falling Body
Report presenting the results of testing in the transonic range of four flutter airfoils attached to a freely falling body. Failures of the airfoils were metered and recorded in order to determine the Mach numbers and altitudes of failure.
Date:
May 5, 1947
Creator:
Barmby, J. G. & Clevenson, S. A.
System:
The UNT Digital Library
Indirect Methods for Obtaining Ram-Jet Exhaust-Gas Temperature Applied to Fuel-Metering Control
Memorandum presenting an analytical method developed that gives two independent means of obtaining the total-temperature ratio across a ram jet or across a turbojet tail-pipe burner without direct measurement of the final gas temperature. Experimental verification of the analysis has been obtained with a 20-inch ram jet over a wide range of operating conditions.
Date:
January 14, 1948
Creator:
Perchonok, Eugene; Sterbentz, William H. & Moore, Stanley H.
System:
The UNT Digital Library
A comparison with flight data of vertical-tail loads in various maneuvers estimated from sideslip angles and rudder deflections
Report presenting a comparison of the vertical-tail loads determined from pressure-distribution measurements in flight in various maneuvers with the corresponding vertical-tail loads. Some of the maneuvers investigated included slow rolls, steady sideslips, fishtails, and rolling pull-outs.
Date:
December 11, 1947
Creator:
Turner, Howard L.
System:
The UNT Digital Library
Measurements of Static and Total Pressure Throughout the Transonic Speed Range as Obtained from an Airspeed Head Mounted on a Freely Falling Body
"Results of tests of an airspeed head mounted on a freely falling body are presented in preliminary form. Measurements were made throughout the transonic speed range. Details and dimensions of the airspeed head and the body are given in figure 1" (p. 1).
Date:
April 24, 1947
Creator:
Mathews, C. W. & Thompson, J. R.
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
Increase in Stable-Air-Flow Operating Range of a Mixed-Flow Compressor by Means of a Surge Inhibitor
Report presenting an investigation of a surge inhibitor that was able to cause a considerable gain in stable-airflow operating range over the range of equivalent impeller tip speeds tested. While the inhibitor was designed to triple the stable-airflow operating range, it increased it more than eight times its original value.
Date:
April 3, 1947
Creator:
Laskin, Eugene B. & Kofskey, Milton G.
System:
The UNT Digital Library
A suggested method of analyzing for transonic flutter of control surfaces based on available experimental evidence
Report presenting the results of a study of the movement of shocks on a three-dimensional wing with and without aileron flutter occurring. The studies include a number of changes and variations to the wing and control. Results for the standard wing and aileron, spoilers at 50 percent chord, upper and lower surface, faired bumps at the 50-percent-chord and 70-percent-chord positions, variations of thickness ratio along the span, vent holes between upper and lower surface, aileron-contour change, aileron mass overbalance, dampers, wing flutter, buffeting forces on fixed controls, and static characteristics are provided.
Date:
December 16, 1947
Creator:
Erickson, Albert L. & Stephenson, Jack D.
System:
The UNT Digital Library