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The relationship between education and job satisfaction is investigated and defined in social-psychological terms in this report. The objective of the research was to test the assumption that the better an individual's education, the greater his chances of securing a desired and satisfying job. The authors found a general scarcity of specific information on this relationship and employed two sources of related information in their research. First, they analyzed 16 previous studies which dealt with the relationship between the two variables. Second, they examined secondary analyses of nine national surveys of the American work force. Findings for noncollege trained workers indicated that no increment in job satisfaction exists with each succeeding year of education and that no relationship exists between educational level and job satisfaction. Also indicated was that those persons who had obtained college degrees were consistently more satisfied with their jobs than were other workers. On the basis of these and other findings, the report concludes with a series of six recommendations for future research and policy changes. They include investigating the occupational needs of overeducated workers, reexamining the educational requirements for jobs, and redesigning jobs. The authors developed a social-psychological model to help them understand the relationship between education and job satisfaction. In this model, they reasoned that educational level should be positively related to quality of employment (how good one's pay is, how convenient the hours are, how interesting the work is). (Author/DB)

Data obtained from a national, cross-sectional survey of the American work force were used to examine the relationship between age and an interview measure of psychological involvement with work (i.e., paid employment). For men, this relationship was curvilinear. Commitment began at a low level among the 16-20 year old men, rose to its highest point among those 30-44 years old, and then declined back to its initially low level among those 55-65 years old. Age was not significantly related to the work commitment of women. Changes in quality of employment through the life cycle were, for men, found to be one determinant of correspondence changes in work commitment. No matter how good or bad men's jobs were in the early part of their working lives, most men ended up with a fairly low degree of committent just prior to retirement age. The concept of anticipatory desocialization from the work role was used to explain the latter finding. (Author)

This appendix to the final report of a study on effectiveness in work roles contains nine methodological appendixes that provide the technical details of the measures used in the five-year study. (CE 016 655 is the final report.) Appendixes A and B are reproductions of the interview schedules for phases 1 and 2 and appendixes C and D reproduce the question booklets respondents were asked to fill out in phases 1 and 2, respectively. Appendix E depicts the rating scales which supervisors were asked to fill out concerning their subordinates in phase 1. Appendix F does the same for Phase 2. Appendix G spells out the procedures followed by the observers in phase 1 and includes a list of all rating scales employed. Appendix H provides similar information on the observations in phase 2. Appendix I presents the brief interview schedule used in phase 2 for a telephone follow-up of respondents who had left their original employers. (JH)

A five-year study of effectiveness in work roles had four general objectives: (1) to assess associations between aspects of working conditions and indicators of employees' work role effectiveness; (2) to identify personal and situational characteristics that limit associations between working conditions and effectiveness; (3) to begin to map the statistical structure of associations among various classes of effectiveness measures; and (4) to assess the validity of effectiveness indicators when measured in different ways and tested against different causal factors. Major methodological findings were that information from different sources regarding working conditions and worker behavior is in agreement only for relatively unambiguous and external aspects of work. As the abstractness and, thus, potential ambiguity of a measure increase, assessments from workers, observers, and supervisors become increasingly liable to judgmental biases, such as the halo effect. Major substantive results include identification of stress effects upon worker attitudes and behaviors, including a withdrawal syndrome that begins with frequent absences and culminates in voluntary turnover. (Twenty-one chapters, each a self-contained paper including methodological information and citation of sources, comprise this final report. It is divided into two parts. Part I presents chapters on methodological topics including defining, measuring, and assessing the quality of employment, and assessing work environments with observational methods. Part II, employee responses to work environments, has three sections: work role stress and strain; motivation and rewards; and compatibility of work roles and life roles. A methodological appendix is available separately as CE 016 610.) (Author/JH)

The sourcebook of tables presents basic descriptive statistics on all questions asked in the 1972-73 Quality of Employment Survey. Based on the Survey of Working Conditions 1969-70, this second survey obtained data from the same population and repeated the same core measures, with some adjustment. Data for the survey were obtained through personal interviews with 1,496 persons 16 years of age or older, and employed for pay for 20 or more hours a week. General survey methodology and outcome measures are discussed. Tables are grouped into the following area: comparisons among labor standard problem areas, wages and wage loss, hours and other time-related problems, health and safety, transportation to and from work, unions, discrimination, employment agencies, job security, supervision and interpersonal relations, promotions, content of work, meaning of work, and personal characteristics. The article, "Evaluating Working Conditions in American: Is the Sky Really Falling?" summarizes many of the 1973 Survey statistics, and is presented in full. The full 1972-73 survey interview, including the page number in the document that shows the appropriate descriptive statistics for each question, and an updated version of the documentary products for the 1969-70 and the 1972-73 surveys are appended. (LH)

Ways that the language laboratory can help meet the needs of department chairs, faculty members, and students are discussed. The use of media in teaching, planning new laboratories, coordinating coursework and labwork, and keep current are covered. A description of the Millsaps College lab and sources of information are appended. (Contains 30 references.) (LB)

Comparative studies were performed on the heat-shielding characteristics of honeycomb-core sandwich panels fabricated with different materials for possible use as wall panels for the proposed crew exploration vehicle. Graphite/epoxy sandwich panel was found to outperform aluminum sandwich panel under the same geometry due to superior heat-shielding qualities and lower material density. Also, representative reentry heat-transfer analysis was performed on the windward wall structures of a generic crew exploration vehicle. The Apollo low Earth orbit reentry trajectory was used to calculate the reentry heating rates. The generic crew exploration vehicle has a graphite/epoxy composite honeycomb sandwich exterior wall and an aluminum honeycomb sandwich interior wall, and is protected with the Apollo thermal protection system ablative material. In the thermal analysis computer program used, the TPS ablation effect was not yet included; however, the results from the nonablation heat-transfer analyses were used to develop a "virtual ablation" method to estimate the ablation heat loads and the thermal protection system recession thicknesses. Depending on the severity of the heating-rate time history, the virtual ablation period was found to last for 87 to 107 seconds and the ablation heat load was estimated to be in the range of 86 to 88 percent of the total heat load for the ablation time period. The thermal protection system recession thickness was estimated to be in the range of 0.08 to 0.11 inches. For the crew exploration vehicle zero-tilt and 18-degree-tilt stagnation points, thermal protection system thicknesses of h = {0.717, 0.733} inches were found to be adequate to keep the substructural composite sandwich temperature below the limit of 300 F.

This report deals with hypothetical reentry thermostructural performance of the Space Shuttle orbiter with missing or eroded thermal protection system (TPS) tiles. The original STS-5 heating (normal transition at 1100 sec) and the modified STS-5 heating (premature transition at 800 sec) were used as reentry heat inputs. The TPS missing or eroded site is assumed to be located at the center or corner (spar-rib juncture) of the lower surface of wing midspan bay 3. For cases of missing TPS tiles, under the original STS-5 heating, the orbiter can afford to lose only one TPS tile at the center or two TPS tiles at the corner (spar-rib juncture) of the lower surface of wing midspan bay 3. Under modified STS-5 heating, the orbiter cannot afford to lose even one TPS tile at the center or at the corner of the lower surface of wing midspan bay 3. For cases of eroded TPS tiles, the aluminum skin temperature rises relatively slowly with the decreasing thickness of the eroded central or corner TPS tile until most of the TPS tile is eroded away, and then increases exponentially toward the missing tile case.

This report describes a method that can calculate transient aerodynamic heating and transient surface temperatures at supersonic and hypersonic speeds. This method can rapidly calculate temperature and heating rate time-histories for complete flight trajectories. Semi-empirical theories are used to calculate laminar and turbulent heat transfer coefficients and a procedure for estimating boundary-layer transition is included. Results from this method are compared with flight data from the X-15 research vehicle, YF-12 airplane, and the Space Shuttle Orbiter. These comparisons show that the calculated values are in good agreement with the measured flight data.

Around 1970, the Y-F-12A loads and structures efforts focused on numerous technological issues that needed defining with regard to aircraft that incorporate hot structures in the design. Laboratory structural heating test technology with infrared systems was largely created during this program. The program demonstrated the ability to duplicate the complex flight temperatures of an advanced supersonic airplane in a ground-based laboratory. The ability to heat and load an advanced operational aircraft in a laboratory at high temperatures and return it to flight status without adverse effects was demonstrated. The technology associated with measuring loads with strain gages on a hot structure was demonstrated with a thermal calibration concept. The results demonstrated that the thermal stresses were significant although the airplane was designed to reduce thermal stresses. Considerable modeling detail was required to predict the heat transfer and the corresponding structural characteristics. The overall YF-12A research effort was particularly productive, and a great deal of flight, laboratory, test and computational data were produced and cross-correlated.

A boundary-layer transition is proposed for a future flight mission of the air-launched Pegasus space booster. The flight experiment requires attaching a glove assembly to the wing of the first-stage booster. The glove design consists of a spring and hook attachment system which allows for thermal growth of a steel 4130 skin. The results from one- and two-dimensional thermal analyses of the initial design are presented. Results obtained from the thermal analysis using turbulent flow conditions showed a maximum temperature of approximately 305 C and a chordwise temperature gradient of less than 8.9 C/cm for the critical areas in the upper glove skin. The temperatures obtained from these thermal analyses are well within the required temperature limits of the glove.

A real-time heating algorithm was derived and installed on the Ames Research Center Dryden Flight Research Facility real-time flight simulator. This program can calculate two- and three-dimensional stagnation point surface heating rates and surface temperatures. The two-dimensional calculations can be made with or without leading-edge sweep. In addition, upper and lower surface heating rates and surface temperatures for flat plates, wedges, and cones can be calculated. Laminar or turbulent heating can be calculated, with boundary-layer transition made a function of free-stream Reynolds number and free-stream Mach number. Real-time heating rates and surface temperatures calculated for a generic hypersonic vehicle are presented and compared with more exact values computed by a batch aeroheating program. As these comparisons show, the heating algorithm used on the flight simulator calculates surface heating rates and temperatures well within the accuracy required to evaluate flight profiles for acceptable heating trajectories.

Structural performance and resizing of the finite-element thermal analysis computer program was used in the reentry heat transfer analysis of the space shuttle orbiter. One midfuselage cross section and one midspan wing segment were selected to study the effects of internal convection and internal radiation on the structural temperatures. The effect of internal convection was found to be more prominent than that of internal radiation in the orbiter thermal analysis. Without these two effects, the calculated structural temperatures at certain stations could be as much as 45 to 90 percent higher than the measured values. By considering internal convection as free convection, the correlation between the predicted and measured structural temperatures could be improved greatly.

Structural temperatures and thermal protection system surface temperatures were measured on the space shuttle during the flight of STS 5. The measured data are compared with values calculated at wing stations 134, 240, and 328 and at fuselage station 877. The theoretical temperatures were calculated using the structural performance and resizing finite element thermal analysis program. The comparisons show that the calculated temperatures are, generally, in good agreement with the measured data.

Structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat transfer analysis of the Space Shuttle Orbiter wing subjected to reentry aerodynamic heating. With sufficient external forced convective cooling near the end of the heating cycle, the calculated surface temperatures of the thermal protection system (TPS) agree favorably with the flight data for the entire flight profile. However, the effects of this external forced convective cooling on the structural temperatures were found to be negligible. Both free convection and forced convection elements were introduced to model the internal convection effect of the cool air entering the Shuttle interior. The introduction of the internal free convection effect decreased the calculated wing lower skin temperatures by 20 F at most, 1200 sec after touchdown. If the internal convection is treated as forced convection, the calculated wing lower skin temperatures after touchdown can be reduced to match the flight-measured data very closely. By reducing the TPS thicknesses to certain effective thickness to account for the TPs gap heating, the calculated wing lower skin temperatures prior to touchdown can be raised to agree with the flight data perfectly.

A structural performance and resizing (SPAR) finite-element thermal analysis computer program was used in the heat-transfer analysis of the space shuttle orbiter subjected to reentry aerodynamic heating. Three wing cross sections and one midfuselage cross section were selected for the thermal analysis. The predicted thermal protection system temperatures were found to agree well with flight-measured temperatures. The calculated aluminum structural temperatures also agreed reasonably well with the flight data from reentry to touchdown. The effects of internal radiation and of internal convection were found to be significant. The SPAR finite-element solutions agreed reasonably well with those obtained from the conventional finite-difference method.