Scielo RSS <![CDATA[Journal of Aerospace Technology and Management]]> http://www.scielo.br/rss.php?pid=2175-914620190001&lang=en vol. 11 num. lang. en <![CDATA[SciELO Logo]]> http://www.scielo.br/img/en/fbpelogp.gif http://www.scielo.br <![CDATA[The Impact of Delays on Customers' Satisfaction: an Empirical Analysis of the British Airways On-Time Performance at Heathrow Airport]]> http://www.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100300&lng=en&nrm=iso&tlng=en ABSTRACT: Increased congestion at hub airports affects on-time airline performance to the detriment of customer satisfaction and may have substantially negative repercussions for airlines in a hypercompetitive environment. This paper concentrates on the on-time performance of British Airways (BA) at London Heathrow Airport (LHR) to identify BA's delays/disruption management; measure the passengers' expectations in case of a delay; and investigate the passenger satisfaction levels. A survey of 160 BA passengers based on a close-ended questionnaire was conducted, complemented by semi-structured interviews with four members of staff at BA's network operations department. The survey results show that BA has been able to satisfy its customers by matching or exceeding their expectations and that those customers will travel with BA again.Interestingly, the results contradict the widespread belief that BA passengers are annoyed by a service failure/delay at LHR; this is because they expect to experience such a delay anyway. <![CDATA[Experimental and Numerical Study of the Unsteady Wake of a Supercritical Airfoil in a Compressible Flow]]> http://www.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100301&lng=en&nrm=iso&tlng=en ABSTRACT Experimental investigations were carried out to study the wake profile of a supercritical airfoil at Mach numbers of 0.4 and 0.6 in a pitching motion. Both static and dynamic tests were conducted in a tri-sonic wind tunnel. Flow field inside the wake was measured by hot wire anemometry at downstream distances of 0.25 and 0.5 times the chord length from trailing edge. All data were taken at mean incidence angle of 3º; the amplitude of oscillation was 3º and the oscillation frequencies were 3 and 6 Hz. Moreover, numerical study was applied for the same airfoil under similar experimental test conditions; finally, wake profiles obtained from both numerical and experimental methods were compared.