Kiwifruits are often exposed to various temperature fluctuation (TF) during postharvest storage. To evaluate the effect of TF on the qualities of kiwifruits, fruits were stored at 2 ºC, 2 ºC or 5 ºC (TF2ºC-5ºC), 2 ºC or 7 ºC (TF2ºC-7ºC), alternating every 12 h. Observations revealed that kiwifruits stored at constant 2 °C showed the lowest loss of weight and vitamin C due to the minimum ethylene production and respiratory rate compared to that of TF2ºC-5ºC and TF2ºC-7ºC. Moreover, the results of RT-qPCR verifed that the expression of genes encoding polygalacturonase, β-galacturonidase, and pectin methyl esterase was significantly increased by the treatment of TF. Hence, TF accelerated the degradation of the cell walls, softening, translucency and relative conductivity of the flesh of kiwifruits. Besides, the impact of TF2ºC-7ºC on kiwifruits was more significant relative to TF2ºC-5ºC. The present study provides a theoretical basis for kiwifruit during cold storage.

The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs. At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities using an engineering flight simulator and as such, to identify potential design solutions which will enhance its controllability and manoeuvrability characteristics. This aircraft is aimed toward the commercial sector with a range of 3,000 nautical miles, carrying a payload of 20,000kg. In the engineering flight simulator a flight test was undertaken; first, to determine the BWB design’s static stability through a standard commercial mission profile, and then to determine its dynamic stability characteristics through standard dynamic modes. Its flying qualities suggested its stability with a static margin of 8.652% of the Mean Aerodynamic Chord (MAC) and consistent response from the pilot input. In addition, the aircraft achieved a maximum lift-to-drag ratio of 28.1; a maximum range of 4,581 nautical miles; zero-lift drag of 0.005; and meeting all the requirements of the dynamic modes.