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The purpose of this paper is to focus on the Fédération Internationale des Ingénieurs‐Conseils (FIDIC) White Book standard form of building contract. It tracks the changes to this contract over its four editions, and seeks to identify their underlying causes.

The changes made to the White Book are quantified using a specific type of quantitative content analysis. The amended clauses are then examined to understand the nature of the changes made.

The length of the contract increased by 34 per cent between 1990 and 2006. A large proportion of the overall increase can be attributed to the clauses dealing with “conflict of interest/corruption” and “dispute resolution”. In both instances, the FIDIC drafting committees have responded to international developments to discourage corruption, and to encourage the use of alternative dispute resolution. Between 1998 and 2006, the average length of the sentences increased slightly, raising the question of whether long sentences are easily understood by users of contracts.

Quantification of text appears to be particularly useful for the analysis of documents which are regularly updated because changes can be clearly identified and the length of sentences can be determined, leading to conclusions about the readability of the text. However, caution is needed because changes of great relevance can be made to contract clauses without actually affecting their length.

The paper will be instructive for contract drafters and informative for users of FIDIC's White Book.

Quantifying text has been rarely used regarding standard‐form contracts in the field of construction.

This paper aims to deal with the numerical investigation of laminar separation bubble (LSB) characteristics (length and height of the bubble) of SS007 airfoil at the chord Reynolds number of Re_c = 0.68 × 10⁵ to 10.28 × 10⁵.

The numerical simulations of the flow around SS007 airfoil were carried out by using the commercial fluid dynamics (CFD) software, ANalysis system (ANSYS) 15. To solve the governing equations of the flow, a cell-centred control volume space discretisation approach is used. Wind tunnel experiments were conducted at the chord-based Reynolds number of Re_c = 1.6 × 10⁵ to validate the aerodynamic characteristics over SS007 airfoil.

The numerical results revealed that the LSB characteristics of a SS007 airfoil, and the aerodynamic performances are validated with experimental results. The lift and drag coefficients for both numerical and experimental results show very good correlation at Reynolds number 1.6 × 10⁵. The lift coefficient linearly increases with the increasing angle of attack (AOA) is relatively small. The corresponding drag coefficient was found to be very small. After the formation of LSB which leads to burst to cause airfoil stall, the lift coefficient decreases and increases the drag coefficient.

Low Reynolds number and LSB characteristics concept in aerodynamics is predominant for both civilian and military applications. These include high altitude devices, wind turbines, human powered vehicles, remotely piloted vehicles, sailplanes, unmanned aerial vehicle and micro aerial vehicle. In this paper, the micro aerial vehicle flight conditions considered and investigated the LSB characteristics for different Reynolds number. To have better aerodynamic performances, it is strongly recommended to micro aerial vehicle (MAV) design engineers that the MAV is to fly at 12 m/s (cruise speed).

MAVs and unmanned aerial vehicles seem to give some of the technical challenges of nature conservation monitoring and law enforcement a versatile, reliable and inexpensive solution.

The SS007 airfoil delays the flow separation and improves the aerodynamic efficiency by increasing the lift and decreasing the drag. The maximum increase in aerodynamic efficiency is 12.5% at stall angle of attack compared to the reference airfoil at Re = 2 × 10⁵. The results are encouraging and this airfoil could have better aerodynamic performance for the development of MAV.

Subcontracting is a crucial cause behind the simultaneous existence of formal and informal entrepreneurship in India. This article aims to provide an over-time comparative analysis between the subcontracted and the non-subcontracted enterprises within the informal sector. Further, it also brings to fore the contribution of subcontracting towards ensuring sustainability of the informal enterprises.

By constructing a panel data from two rounds of NSS Unincorporated Enterprise Survey Data (2010 and 2015), and employing a PSM-DID method, considering labour productivity and net retained earnings as two critical indicators of growth and development of the informal sector firms, this study has made some broad claims regarding the differences in immediate and long run performances between the subcontracted and non-subcontracted informal sector enterprises in India.

This study finds that subcontracted enterprises have not only been performing at a much lower level than the non-subcontracted enterprises, they are also growing much slowly than their counterparts. However, it has been observed that for the establishments, who are capital abundant and also have a larger production capacity, subcontracting is showing the prospect for deriving sustainable gains.

This article contributes to the existing literature in the following two ways. Firstly, it provides an over-time comparative analysis between the subcontracted and the non-subcontracted enterprises within the informal sector. Secondly, it brings to fore the contribution of subcontracting towards ensuring sustainability of the informal enterprises.

Rainfall is one of the main atmospheric conditions that significantly affect the aerodynamic performance of the low Reynolds number flights. In this paper, the adverse effects of rain on the aerodynamic performance of a two-dimensional (2D) airfoil with a chord-based low Reynolds number of 2 × 10⁵ and the mini-unmanned aerial vehicle (UAV) for various flight conditions, i.e. 0°–40° at Mach number 0.04 were studied numerically. The purpose of this study is to explore the aerodynamic penalties that affect the liquid water content (LWC = 5.33) of the airfoil and UAV performance in rain under different flying conditions.

The Eulerian–Lagrangian two-phase flow method is adopted to simulate the rain environment over an airfoil and mini-UAV aerodynamic performances. The Reynolds Averaged Navier–Stokes equations are considered to solve the time-averaged equations of motion for fluid flow.

The effect of rainfall on the airfoil and mini-UAV is studied numerically and validated experimentally. For 2D airfoil, the lift and drag coefficients for both numerical and experimental results show a very good correlation at Reynolds number 2 × 10⁵. For three-dimensional (3D) mini-UAV, the lift and drag coefficients for both numerical and experimental results show a very good correlation at Mach number 0.04. The raindrops distribution around the airfoil, premature trailing edge separation, boundary-layer velocity profiles at five different chord positions (i.e. LE, 0.25c, 0.5c, 0.75c and 0.98c) on the upper surface of the airfoil, water film height and the location of rivulet formation on the upper surface of the airfoil are also presented.

For 2D airfoil, the recorded maximum variation of the coefficient of lift and lift-to-drag (L/D) ratio is observed to be 5.33% at an 8° and 10.53% at a 4° angle of attack (AOA) between numerical and experimental results under the influence of rainfall effect for LWC = 5.33. The L/D ratio percentage degradation is seen to be 61.9% at an AOA of 0°–2° for the rain environment. For 3D mini-UAV, the recorded maximum variation of the coefficient of lift and L/D ratio are observed to be 2.84% and 4.60% at a 30° stall AOA under the influence of rainfall effect for LWC = 5.33. The numerical results are impressively in agreement with the experimental results. UAV designers will benefit from the findings presented in this paper. This will be also helpful for training the pilots to control the airplanes in a rain environment.

Building a quality teaching force depends fundamentally upon attracting suitable candidates into teaching. This translates into transparent and clear policies and procedures for recruitment and transfers. Teacher recruitment and transfer are significant aspects of teacher management in Indian states because of the size and the differences that exist in different locations, in terms of facilities including access to health care services, higher educational institutions, and also transport and mobility. The presence or absence of these facilities and services determine the perceived quality for teachers, especially as it also determines their and the family members’ (including spouse and children) ability to access education, health care, or job market. This makes the recruitment and transfer policy a critical aspect of teacher management that contributes significantly to the motivation and job satisfaction of the teacher. Karnataka was able to make progress on designing and implementing transparent and effective teacher recruitment and transfer policies and move away from a system plagued by the weaknesses exhibited by other states. This chapter undertakes a historical analysis of teacher recruitment and transfers in the state, examines the determinants that led to current policies and an examination of the on-going changes since the policy was first introduced. Using Karnataka’s example, it argues that effective and efficient teacher management systems can lead to better teacher quality.

The purpose of this study is to analyse numerically and experimentally the effects of lip thickness (LT) and bypass ratio on co-flowing nozzle under subsonic and correctly expanded sonic jet decay at different Mach numbers.

Co-flowing jets from co-flowing nozzles of different LTs, 0.2, 1 and 1.5 Dp (where Dp is the primary nozzle exit diameter = 10 mm), with an annular gap of 10 mm at main jet exit Mach numbers 0.6 have been studied experimentally and the other cases have been performed numerically. The co-flowing jet with 2 mm LT was used for comparison.

Co-flowing jet axial pitot pressure decay, axial static pressure decay, axial velocity decay, radial velocity decay and streamline velocity contours were analyzed. The results illustrate that the mixing of the co-flowing jet with profound LT is prevalent to the co-flowing jet with 2 mm LT, at all Mach numbers of the current study. Also, the LT of the co-flowing jet has a strong impact on jet mixing. Co-flowing jets with 10 mm and 15 mm LT with a constant co-flow width of 10 mm experience a considerably advanced mixing than co-flowing jets with 2 mm LT and a co-flow width of 10 mm.

The application of bypassed co-flow jet is in turbofan engine operates efficiently in modern civil aircraft.

All subsonic jets are considered correctly expanded with negligible variation in axial static pressure. However, in the present study, static pressure along the centerline varies sinusoidally up to 9% and 12% above and below atmospheric pressure, respectively, for primary jet exit Mach number 1.0. The sinusoidal variation is less for primary jet exit Mach numbers 0.6 and 0.8 in static pressure decay.

The effect of increasing lip thickness (LT) and Mach number on subsonic co-flowing Jet (CFJ) decay at subsonic and correctly expanded sonic Mach numbers has been analysed experimentally and numerically in this study. This study aims to a critical LT below which mixing enhances and above which mixing inhibits.

LT is the distance, separating the primary nozzle and the secondary duct, present in the co-flowing nozzle. The CFJ with LT ranging from 2 mm to 150 mm at jet exit Mach numbers of 0.6, 0.8 and 1.0 were studied in detail. The CFJ with 2 mm LT is used for comparison. Centreline total pressure decay, centreline static pressure decay and near field flow behaviour were analysed.

The result shows that the mixing enhances until a critical limit and a further increase in the LT does not show any variation in the jet mixing. Beyond this critical limit, the secondary jet has a detrimental effect on the primary jet, which deteriorates the process of mixing. The CFJ within the critical limit experiences a significantly higher mixing. The effect of the increase in the Mach number has marginal variation in the total pressure and significant variation in static pressure along the jet axis.

In this study, the velocity ratio (VR) is maintained constant and the bypass ratio (BR) was varied from low value to very high values for subsonic and correctly expanded sonic. Presently, commercial aircraft engine operates under these Mach numbers and low to ultra-high BR. Hence, the present study becomes essential.

This is the first effort to find the critical value of LT for a constant VR for a Mach number range of 0.6 to 1.0, compressible CFJ. The CFJs with constant VR of unity and varying LT, in these Mach number range, have not been studied in the past.

The reduction in under nutrition is very slow in the past two decades in India even with high-economic growth rate and expansion in the ICDS programme. The ICDS evaluation studies majorly stressed on the general factors but they fail to acknowledge the structural factors - class and caste - while providing solutions. In Tamil Nadu nutritional status and utilization of ICDS services are better as compared to all-India average. The purpose of this paper is to explore the nutritional status of the poor and scheduled caste (SC) in Tamil Nadu and their utilization of ICDS services and to examine the role of group-specific factors in low reduction of nutritional status and utilization of ICDS programme.

Multivariate analysis and logistic regression method were used using SPSS.

The reduction of underweight is slow among the poorest and SC, moreover, the disparity between the richest and poorest as well as upper caste and SC is increasing. Logistic regression analysis shows that the poorest are marginalized, children belonging to poorer income group have higher chances of using the ICDS than the poorest and it is significant. After making the wealth quintile constant, the utilization of ICDS services across social groups showed that, though the poorest quintile has less access, within them the SC had utilized less compared to the other backward class (OBC). This indicates the poorest SCs are more vulnerable and marginalized across all quintiles and social groups.

In Tamil Nadu there is no sufficient sample of other caste/tribe and scheduled tribe. It would have given more insight on the utilization pattern. Lack of qualitative data has limited in explaining few phenomena to get more insight.

It will help the government to formulate more inclusive policy and address the issue of exclusion of marginalized people.

The main core argument was based on the Tamil Nadu National Family Health Survey (NFHS) III unit-level data.