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409
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174
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221
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The calculation of pressure on slender airplanes in subsonic and supersonic flow
"Under the assumption that a wing, body, or wing-body combination is slender or flying at near sonic velocity, expressions are given which permit the calculation of pressure in the immediate vicinity of the configuration. The disturbance field, in both subsonic and supersonic flight, is shown to consist of two-dimensional disturbance fields extending laterally and a longitudinal field that depends on the streamwise growth of cross-sectional area. A discussion is also given of couplings, between lifting and thickness effects, that necessarily arise as a result of the quadratic dependence of pressure on the induced velocity components" (author).
Date:
March 1953
Creator:
Heaslet, Max A. & Lomax, Harvard
System:
The UNT Digital Library
Water-landing investigation of a flat-bottom v-step model and comparison with a theory incorporating planing data
Report presenting testing of a flat-bottom V-step model with a beam loading of 4.6 subjected to fixed-trim impacts in smooth water. Testing occurred at three different trim angles and a range of initial flight-path angles. Data were obtained as time histories of draft, vertical velocity, and vertical acceleration. The results are presented as plots of nondimensional lift, draft, vertical velocity, and time against flight-path angle at contact.
Date:
May 1953
Creator:
Miller, Robert W.
System:
The UNT Digital Library
Impingement of water droplets on a cylinder in an incompressible flow field and evaluation of rotating multicylinder method for measurement of droplet-size distribution, volume-median droplet size, and liquid-water content in clouds
Report presenting an evaluation of the rotating multicylinder method for the measurement of droplet-size distribution, volume-median droplet size, and liquid-water content in clouds, which showed that small uncertainties in the basic data eliminate the distinction between cloud droplet-size distributions and are a source of large errors in the determination of droplet size. Matching curves for obtaining droplet-size distribution, volume-median droplet size, and liquid-water content from flight data were computed from the results of the droplet-trajectory configurations.
Date:
March 1953
Creator:
Brun, Rinaldo J. & Mergler, Harry W.
System:
The UNT Digital Library
An analysis of the factors affecting the loss in lift and shift in aerodynamic center produced by the distortion of a swept wing under aerodynamic load
From Introduction: "The importance of this aeroelastic phenomenon has been recognized for some time, and several investigators have developed more or less refined methods for analysis of wing elastic distortions and their effects. (For examples, see refs. 1 to 4.) More specific evidence as to the influence of wing external geometry (in conjunction with flight condition) on this flexibility-longitudinial-stability problem would appear to be of interest to the aerodynamicist, however, so that he can obtain rough indications as to which wing plan forms would be practical from aeroelastic considerations."
Date:
March 1953
Creator:
Mathews, Charles W. & Kurbjun, Max C.
System:
The UNT Digital Library
Strength analysis of stiffened thick beam webs with ratios of web depth to web thickness of approximately 60
"The results of an experimental investigation of the strength of plane diagonal-tension webs with ratios of web depth to web thickness of about 60 are presented. An analysis of the beam indicated that the methods of strength analysis presented in NACA TN 2661 are applicable to beams with flanges symmetrically arranged with respect to the web if the portal-frame effect is taken into account" (p. 1).
Date:
May 1953
Creator:
Levin, L. Ross
System:
The UNT Digital Library
Matrix methods for determining the longitudinal-stability derivatives of an airplane from transient flight data
Report presenting three matrix methods for determining the longitudinal-stability derivatives from transient flight data. The results obtained for the methods presented depend in a large measure on accurate instrument measurements and require considerable computation to yield adequate engineering answers.
Date:
March 1953
Creator:
Donegan, James J.
System:
The UNT Digital Library
Effects of Parallel-Jet Mixing on Downstream Mach Number and Stagnation Pressure With Application to Engine Testing in Supersonic Tunnels
"A one-dimensional analysis of the results of the parallel-jet mixing encountered in the testing of engines in supersonic wind tunnels is reported. Equations were derived for determining the totla pressure and Mach number behind the tunnel terminal shock. The method represents a simple procedure for determining these quantities while a tunnel is still in the design stage" (p. 1).
Date:
March 1953
Creator:
Bernstein, Harry
System:
The UNT Digital Library
The asymmetric adjustable supersonic nozzle for wind-tunnel application
Report presenting the development of an asymmetric type of adjustable supersonic nozzle suitable for application to wind tunnels. This type of nozzle permits continuous adjustment of the test-section Mach number without the requirement of flexible walls.
Date:
March 1953
Creator:
Allen, H. Julian
System:
The UNT Digital Library
Impingement of water droplets on wedges and diamond airfoils at supersonic speeds
"An analytical solution has been obtained for the equations of motion of water droplets impinging on a wedge in a two-dimensional supersonic flow field with a shock wave attached to the wedge. The closed-form solution yields analytical expressions for the equation of the droplet trajectory, the local rate of impingement and the impingement velocity at any point on the wedge surface, and the total rate of impingement. The analytical expressions are utilized to determine the impingement on the forward surfaces of diamond airfoils in supersonic flow fields with attached shock waves" (p. 1).
Date:
July 1953
Creator:
Serafini, John S.
System:
The UNT Digital Library
Interim Report on a Fatigue Investigation of a Full-Scale Transport Aircraft Wing Structure
Note presenting results of an investigation of the fatigue strength of several full-scale aircraft wing structures. The 34 fatigue failures which resulted from the tests were of four main types and occurred in three principal localities on the test wings. Results regarding the definition of fatigue failure, load history of specimens, description of fatigue failures, spread in fatigue life, stress concentration factors, rate of crack growth, and effect of fatigue damage on natural frequency and damping are provided.
Date:
April 1953
Creator:
McGuigan, M. James, Jr.
System:
The UNT Digital Library
Theoretical pressure distribution and wave drags for conical boattails
"Afterbody pressure distributions and wave drag were calculated using a second-order theory for a variety of conical boattails at zero angle of attack. Results are presented for Mach numbers from 1.5 to 4.5, area ratios from 0.200 to 0.800, and boattail angle from 3 degrees to 11 degrees. The results indicate that for a given boattail angle, the wave drag decreases with increasing Mach number and area ratio" (p. 1).
Date:
July 1953
Creator:
Jack, John R.
System:
The UNT Digital Library
The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75
From Introduction: "This paper presents the basic design method and experimental results of calibration of a nozzle which was constructed to conform to the analytically determined ordinates."
Date:
April 1953
Creator:
Burbank, Paige B. & Byrne, Robert W.
System:
The UNT Digital Library
The Design of Variable Mach Number Asymmetric Supersonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines
Report presenting two theoretical procedures for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One is for Mach numbers less than approximately 3 and one is for Mach numbers greater than 3.
Date:
March 1953
Creator:
Syvertson, Clarence A. & Savin, Raymond C.
System:
The UNT Digital Library
Effect of prestraining of recrystallization temperature and mechanical properties of commercial, sintered, wrought molybdenum
Given three presumably identical lots of commercial, sintered, wrought molybdenum, the 1-hour recrystallization temperature of one lot remained above 2900 F by limiting the amount of effective restraining to 35 percent or less. Different recrystallization temperatures were obtained in various atmospheres, the highest in argon and the lowest in hydrogen. Metal thus fabricated and then stress-relieved possessed an ultimate tensile strength at room temperature within 10 percent of metal swaged 99 percent and also possessed equivalent ductility. At 1800 F, equivalent strength and ductility was obtained irrespective of the amount of swaging over the range of 10 to 99 percent.
Date:
July 1953
Creator:
Dike, Kenneth C. & Long, Roger A.
System:
The UNT Digital Library
Estimated power reduction by water injection in a nonreturn supersonic wind tunnel
Report presenting a simplified analysis to estimate the extent to which the pressure ratio and power of a nonreturn supersonic wind tunnel operating in the low supersonic Mach number range can be reduced by the evaporation of water injected into the diffuser. It appears to be possible to reduce the power by as much as 20 percent for a typical example of a tunnel operating at Mach number 1.4.
Date:
January 1953
Creator:
Cooper, Morton & Sevier, John R., Jr.
System:
The UNT Digital Library
Electrostatic spark ignition-source hazard in airplane crashes
Report presenting an investigation of the hazard of igniting airplane crash fires by electrostatic sparks, which are generated when detached airplane parts fly through clouds of dust and fuel mist. Within the limits of variables studied, the rates with which airplane wreckage collected a charge were directly proportional to the rate at which clay dust or fuel mist was intercepted. Results regarding the experimental charging of airplane parts, electrostatic ignition hazard, and investigation of protective coating are provided.
Date:
October 1953
Creator:
Busch, Arthur M.
System:
The UNT Digital Library
Experimental investigation of two-dimensional tunnel-wall interference at high subsonic speeds
Report presenting a determination of the tunnel-wall interference for a two-dimensional-flow, rectangular, closed-throat wind tunnel over a range of Mach numbers. Aerodynamic data obtained showed that the influence of the walls becomes progressively greater with increasing Mach number and increasing chord-height ratio.
Date:
December 1953
Creator:
Knechtel, Earl D.
System:
The UNT Digital Library
Calculations of upwash in the region above or below the wing-chord planes of swept-back wing-fuselage-nacelle combinations
Report presenting a procedure for predicting the upwash components of the upflow angles in the region above or below the wing-chord planes of sweptback wing-fuselage-nacelle combinations. Comparisons of predicted and measured upflow angles are shown for six semispan models with 40 degree sweptback wings.
Date:
February 1953
Creator:
Rogallo, Vernon L. & McCloud, John L., III
System:
The UNT Digital Library
Influence of Rotor-Engine Torsional Oscillation on Control of Gas-Turbine Engine Geared to Helicopter Rotor
"Equations were developed for the torsional motion of a gas-turbine engine geared to a helicopter rotor in which the rotor blades were hinged to the rotor shaft. The rotor system was simplified to yield simple third-order equations that can be used in the analysis of engine control. Comparison of the system response calculated from these equations with the experimentally observed frequency response of a rotor from a 2500-pound helicopter showed satisfactory agreement" (p. 1).
Date:
October 1953
Creator:
Sanders, John C.
System:
The UNT Digital Library
Determination of the Flying Qualities of the Douglas DC-3 Airplane
Report presenting an evaluation of the flying qualities of the Douglas DC-3 airplane to determine its longitudinal and lateral stability and control characteristics and its stalling behavior.
Date:
December 1953
Creator:
Assadourian, Arthur & Harper, John A.
System:
The UNT Digital Library
Creep-Buckling Analysis of Rectangular-Section Columns
Note presenting an extension of an analysis of the creep behavior of a slightly curved pin-ended H-section column under constant load to the slightly curved solid rectangular-section column. The analysis leads to a differential equation for the plastic strains at the midheight cross section.
Date:
June 1953
Creator:
Libove, Charles
System:
The UNT Digital Library
Surveys of the flow fields at the propeller planes of six 40 degree sweptback wing-fuselage-nacelle combinations
Report presenting the flow fields at the propeller planes of six 40 degree sweptback semispan wing-fusleage-nacelle combinations to provide data and to enable the study of the characteristics of the flow fields and their effect on propeller-oscillating aerodynamic loads. Results regarding the propeller flow fields, oscillating aerodynamic loading, and upflow angles at the horizontal center lines of the propeller disks are provided.
Date:
June 1953
Creator:
Rogallo, Vernon L. & McCloud, John L., III
System:
The UNT Digital Library
An Investigation of the Experimental Aerodynamic Loading on a Model Helicopter Rotor Blade
Note presenting pressure distributions measured on a model helicopter rotor blade under hovering and simulated forward-flight conditions. Pressure were recorded at advance ratios of 0.10, 0.22, 0.30, 0.40, and 0.50 for a zero-offset flapping-hinge rotor and at 0.10, 0.22, 0.30, 0.45, 0.60, 0.80, and 1.0 for a lifting rotor with a flapping-hinge offset of 13 percent.
Date:
May 1953
Creator:
Meyer, John R., Jr. & Falabella, Gaetano, Jr.
System:
The UNT Digital Library
The Structure of Turbulence in Fully Developed Pipe Flow
Note presenting measurements made with a hot-wire anemometer in fully developed turbulent flow in a 10-inch pipe at speeds of approximately 10 and 100 feet per second. Emphasis was placed on turbulence and conditions near the wall. Results regarding the mean-energy balance, turbulent-energy balance, energy-spectrum considerations, and some general considerations are provided.
Date:
June 1953
Creator:
Laufer, John
System:
The UNT Digital Library