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NORTHROP CORP HAWTHORNE CA NORAIR DIV
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NORTHROP CORP HAWTHORNE CA NORAIR DIV
A Numerical Procedure for Determining the Combined Viscid-Inviscid Flow Fields Over Generalized Three-Dimensional Bodies. Volume II, Part I. Manual for Computer Program(
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1
edition published
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1968
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英语
and held by
1
library
worldwide
This report describes the methods and computer programs developed for determining the combined viscid-inviscid flow fields over generalized three-dimensional bodies. The inviscid flow field is determined by a three-dimensional method of characteristics program, while the laminar boundary layer is determined by a three-dimensional explicit finite - different method. The complete program, which can treat either ideal - or real-gas flows, is highly automated and provides many optional paths of analysis. This volume of the report (Volume II) discusses in detail the actual computer program. Part I discusses the make up of the input data, the format of the output data, and the estimation of the running time. Also provided in Part I is a dictionary of all essential FORTRAN variables. (Author).
Solid state diffusion bonded tantalum alloy honeycomb panels(
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1
edition published
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1968
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英语
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A program is described for the development of solid state diffusion bonding technology for production of tantalum alloy (T111) honeycomb panels suitable for either hot structural or heat shield applications in aerospace environments. The investigation and selection of appropriate intermediate materials to effect joining at relatively low temperatures and pressures suitable to the panel configurations is discussed. Emphasis was placed on methods suitable for reasonably low-cost processing. Specific manufacturing problem areas encountered, such as forming, welding, and intermediate application, are discussed. Heating, atmosphere control, and pressure application requirements are described and actions taken to satisfy these requirements are reported. A survey of oxidation protective coatings for tantalum alloys is presented with the actual coatings and procedures used in the program being discussed. Structural testing techniques used in evaluating the integrity of the manufactured honeycomb panels are described. Standard analytical procedures employed in determining failure modes and predicted failure stresses are presented. (Author).
Experimental investigations of ground-jet suppression fences for vtol aircraft prepared sites(
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1
edition published
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1968
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英语
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1
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worldwide
An experimental program was conducted to investigate the effectiveness of ground-jet suppression fences mounted on the periphery of a prepared pad for jet VTOL aircraft in order to reduce the effects of ground erosion and particle entrainment beyond the pad, and thereby reduce the pad size requirement. Small-scale tests of a variety of fence configurations were made using single and dual nozzles. Large-scale tests of the better fence configurations were conducted with a model powered by as many as three J85 engines mounted vertically in a pod. (Author).
Cyclic hot-salt stress corrosion of titanium alloys(
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1
edition published
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1967
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英语
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1
library
worldwide
Lfc aircraft design data laminar flow control demonstration program(
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1
edition published
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1967
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英语
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1
library
worldwide
This report presents a description of the engineering methods and procedures used to make the LFC modification (the X-21A airplane); and it includes improvements, such as wing nose modifications, that were developed in the X-21A flight test programs. The LFC suction surface design, as modified for the second airplane, provided almost total laminarization of the wing upper suction surface in the cruise flight condition.
Image evaluation test plan for terminal guidance simulation study program(
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1
edition published
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1963
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英语
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worldwide
The evaluation and recommendation of technical characteristics for a television system yielding a specified picture quality presents a fundamental problem of how to measure and specify the quality of optical images. The criteria of image quality and units in which these are measured or evaluated must have an objective character to permit design engineers to configure the optical and electrical elements of the system.
Theoretical investigations of boundary layer stability(
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1
edition published
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1966
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英语
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The mathematical analysis underlying a Fortran program for calculating the proper solutions of the Orr-Sommerfeld system with sufficient accuracy and economy for applying the resonance theory of transition is described. This program covers spacewise growths, rather than timewise growths as in previous computations, of mainly two-dimensional Fourier components of the motion. It employs various innovations providing as much accuracy from efficient single-precision arithmetic as would be obtained from awkward multiple-precision arithmetic in previous calculation schemes. The source programs and some sample calculations, for the proncipal mode of oscillation of the Blasius boundary layer, are included. The Lees-Lin stability equation for compressible flow have been extended to include the terms involving the component of the mean boundary layer flow perpendicular to the flat plate. At Mach 5 this more than doubled the critical Reynolds number. Allowance was then made for the three-dimensional aspect of the disturbance velocity. The final result was to give good agreement with observed data in the lower branch of the neutral stability curve at Mach 2.2 and Mach 5, fair agreement with the upper branch at Mach 2.2 and large discrepancies with the data in the upper branch at Mach 5. Comparison of experimental determined neutral stability curves with those computed by simplified approximations have disagreed considerably at high Mach numbers on the upper branch, even when agreement was fairly good on the lower branch.
Parametric investigation of vtol hot gas ingestion and induced jet effects in ground proximity(
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1
edition published
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1967
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英语
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worldwide
A large-scale VTOL test bed designed around the Ames Lift Engine Pod was used for ground-proximity tests at the Ames Research Center VTOL test facility, under sponsorship of the Naval Air Systems Command. Objectives were to obtain parametric data on gas ingestion and jet effects experienced by jet-powered VTOL configurations. Results showed that ingestion and induced-lift effects are configuration- and time-dependent; for many configurations the degree of ingestion experienced cannot be tolerated in operational aircraft. This contrasts with results of recent small-scale tests. Wing geometry, size, location; engine arrangement, lift/cruise engine location and pitch attitude have strong influences on ingestion tendencies and jet-induced effects. Near-field temperature environment appears to be influenced by engine arrangement and number of operating engines. Rapid inlet temperature rise with a high temperature distortion at the compressor face sometimes resulted in engine stall. Hot gases expelled from the engine subsequent to stall occasionally caused stalling of adjacent engines. Large induced force levels and moments resulted from near-ground operation of many configurations. Positive- and negative-induced lift were measured. Aerodynamic suckdown results with a single jet-fundamental geometry configuration are in agreement with empirical correlation of small-scale tests. Results showed that transient measurements with rapid-response thermocouple and recording equipment are needed for realistic assessment of VTOL environment and inlet temperature rise caused by ingestion. (Author).
A STUDY OF THE INFLUENCE OF GEOMETRY ON THE STRENGTH OF FATIGUE CRACKED PANELS(
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1
edition published
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1966
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英语
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worldwide
The objectives of the study program were to define and verify a synthesis of strength-limiting parameters for fatigue cracked panels which would be applicable to the wide range of conditions of interest in the engineering problem of strength analysis and to present this synthesis in a form that would lead to a better conceptual understanding of the interaction between parameters. The program consisted of an analytical study and a supporting experimental study. The analytical study, governed by the above objectives, considered fracture in the elastic range with buckling restraint provided, fracture combined with net section and gross section yielding, and fracture in the elastic range for unrestrained panels. The design problem involving appreciable amounts of slow tear was also considered. The experimental program provided supporting information on the behavior of fatigue cracks for bare 2024-T3 aluminum. Limited test data were also obtained for duplex annealed titanium 8Al-1Mo-1V. The aluminum alloy crack lengths ranged from .5 inch to over 10 inches. Panel widths were thirty, twenty, twelve and nine inches, and nominal panel thicknesses were .080 inch, .063 inch, and .032 inch. The titanium alloy panel widths were twelve and nine inches, and thicknesses were .045 inch and .020 inch. Buckling restraints were used for approximately half of the panels tested. Test information from other sources was used to illustrate specific points in theory and to show the generality of conclusions.
Design calculations on proven trainer and fighter aircraft for the verification of a gust design procedure(
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1
edition published
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1966
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英语
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Design calculations are performed on proven trainer and fighter aircraft for the purpose of verifying a new gust design procedure based on power spectral techniques. The aircraft used in the computation are Northrop Norair T-38 trainer and F-5A fighter. The new gust design procedure uses a gust power spectrum as the input in aircraft response calculation, as against the present discrete gust approach, where the input is a gust velocity profile with a single frequency determined by the aircraft speed and the gust gradient distance. The report describes the specific aircraft weight and flight configurations used in the computation. The choice of stress sensitive locations is explained and illustrated. Also presented is the computation procedure for obtaining the aircraft transfer functions to be used in both the discrete gust and power spectral approaches. Based on the gust input spectrum and the aircraft transfer functions, a number of aircraft gust response power spectra are generated. These latter spectral data are integrated along the frequency band to obtain the mean aircraft response levels and the average zero crossing counts which are the final results of the computation. Through the computation, various scales of turbulence and cut-off frequencies are used to study their effects on the end results of the new gust design procedure.
Empirical correlation of excitation environment and structural parameters with flight vehicle vibration response(
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1
edition published
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1964
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英语
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library
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The design of fatigue resistant structures for high speed aircraft and aerospace vehicles depends largely on the prediction of realistic acoustic, fluctuating aerodynamic, and engine vibration environments and on the estimation of the attendant vibration levels of structural components and attached equipment. The practical engineering limitations on the mathematical and numerical analyses required to treat such structures rigorously by classical dynamics necessitate studies of alternate, approximate methods. In the report, a definitive statement is presented of the empirical approach for determining correlations between the excitation environment and the vibration response of typical flight vehicle structures by means of statistical analyses of measured vibration data. The various aspects of the vibration prediction problem and the general philosophy motivating research in the area of empirical correlation are discussed. Specific treatment is given to the effects of bandwidth, modal density, and surface pressure spacecorrelation on the crosscorrelation of energy transmitted along various structural transmission paths in complex linear structures.
DEVELOPMENT OF MANUFACTURING CAPABILITY FOR PRODUCING HIGH PERFORMANCE ALUMINUM AND MAGNESIUM ALLOY CASTINGS(
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1
edition published
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1964
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This report describes development work on the Mg-Zn-Ag-Zr alloys; further work on aluminum alloys ST60 and M710; development of a modified aluminum alloy 195; Phase II and Phase III configuration pattern; the first founding experience in the Mg-Zn-Ag-Zr alloy, and a general summary of the program development in terms of significance to the program objective.
Simultaneous application of static and dynamic loads on sonic fatigue test articles(
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1
edition published
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1964
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With the existence of the RTD sonic test facility, it becomes necessary to investigate the requirements for reliability fatigue testing during the simulated application of static, dynamic, and acoustic service loadings. The report includes the findings of an extensive investigation of previous combined load failures, documents the existence of such failures and suggests possible future problems based on an industry-wide survey of actual case histories. Analytical substantiation of the increased probability of failure and theoretical acoustic considerations are presented to indicate that combined loads do present a particular problem area. The simulation of static, dynamic, and acoustic loads is discussed in terms of general principles which must be taken into consideration, and general testing methods applicable to difficult and costly vehicle fatigue problems. Limitations and possible future extensions to the RTD sonic test facility are discussed and recommendations presented. Seven specific testing arrangements which have been developed for combined loads simulation of several selected cases are described and illustrated. (Author).
INVESTIGATION OF A METHOD FOR THE PREDICTION OF VIBRATORY RESPONSE AND STRESS IN TYPICAL FLIGHT VEHICLE STRUCTURE. SUPPLEMENT 1 - DYNAMIC MODELING OF COMPLEX STRUCTURES(
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1
edition published
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1963
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The dynamically similar structural model of the preceding contract (See AD-416 784) was redesigned and reworked to improve the simulation. The sandwich structure simulation, the backing board simulation, the intake ducting simulation were improved. Some previously discovered errors in simulation were corrected. The reworked model was then Vibroacoustically tested. The results of this testing were compared to the results of the actual fuselage portion testing of the previous contract. The model was modified to obtain a dynamically similar structural model of the complete XSM-62 Snark missile. The Acoustic (noise) Test Program that was performed on the XSM-62 Snark missile during the design and development of the Snark missile program was duplicated for the model. The model test data was compared to the results of the missile test program. This was done to show the feasibility of such a dynamic modeling method for design of future missile and space vehicle systems.
Terminal guidance simulator study program test. investigation of factors affecting difficulty of target acquisition and identification(
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1
edition published
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1965
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英语
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1
library
worldwide
The purpose of this study was to determine what factors or variables relate to the relative difficulty of the transparencies used in Norair simulation studies. It was assumed that the mean radial miss distance is related to the difficulty of a transparency. It is also assumed that the relative difficulty of a transparency is related to variables thought to be significant in photo-interpretations. This study is then an attempt to relate the relative difficulty of a transparency as measured by the mean radial miss distance of the subjects in Norair Simulation Study and the ratings of ten subjects rating the transparencies in terms of variables used in photo-interpretation. (Author).
NUMERICAL ANALYSIS OF SUPERSONIC FLOW THROUGH CURVED CHANNELS(
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1
edition published
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1963
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英语
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worldwide
An IBM FORTRAN program for calculating supersonic flows through curved channels. Included in the program are: (1) a second order Belotserkovskii procedure for calculating the flow field around the forward part of blunt blades, (2) a general method of characteristics procedure for calculating supersonic flow fields, (3) automatic procedures for calculating interactions of shocks of opposite families, shock interactions with a wall and with a vortex sheet or slipstream, and (4) a finite difference laminar boundary-layer procedure for calculating viscous region of the flow. Three sample calculations as well as the listing of the FORTRAN program are presented.
DEVELOPMENT OF IMPROVED METHODS, PROCESSES, AND TECHNIQUES FOR PRODUCING STEEL EXTRUSIONS(
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1
edition published
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1961
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worldwide
Dimensional integrity and surface qualities obtained in the 0.06-in. tee sections of Phase I ARE CONSIDERED SUFFICIENT FOR PROCEEDING TO Phase II. Low and erratic mechanical properties were noted in the evaluation of Phase I extrusions in both H-11 and PH 15-7Mo materials. Metallurgical studies indicated that these low properties resulted from diffusion of the nickel lubricant material into the surface of the extrusions. After removal of the contaminant coating by chemical etching, the resultant mechanical properties were well within specifications for the materials. The chemical etching also yields improved surface quality.
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