Aerodynamic的問題，透過圖書和論文來找解法和答案更準確安心。 我們找到下列懶人包和總整理

Javelin Boys: Air Defence from the Cold War to Confrontation

為了解決Aerodynamic的問題，作者Bond, Steve 這樣論述：

The Gloster Javelin was the UK’s first line of night and all-weather air defense both at home and in RAF Germany. In the 1950s, when it replaced the Meteor and Venom, this revolutionary bomber interceptor became integral to many great stories told here in terrific detail. With an unorthodox aerodyna

mic design, the Javelin initially had major production issues, which included a tendency for engines to self-destruct under certain conditions. Despite this and the criticism it faced - its nicknames included ’Flying Flat-Iron’ and ’Harmonious Dragmaster’ - the aircraft still receives much affection

from its former aircrew. Starting from the first deliveries of Javelins in 1956 until the final withdrawal from RAF squadron use in 1968, Javelin Boys describes adventures in Cyprus, Singapore during the Indonesian Confrontation and Zambia during the Rhodesian declaration of UDI. In this period a t

otal of 434 Javelins were built, with their use spanning across eighteen different squadrons. Steve Bond has interviewed a number of veterans, all with captivating tales of their time on the aircraft. Alongside their anecdotes is a detailed history of this unusual aircraft, accompanied by photograph

y. This book is bound to appeal to all aviation fans.

Aerodynamic進入發燒排行的影片

低腔壓高濃度過氧化氫混合式火箭引擎之研究

為了解決Aerodynamic的問題，作者林育宏 這樣論述：

本論文為混合式火箭系統入軌段火箭引擎的前期研究，除了高引擎效率的要求外，更需要精準的推力控制與降低入軌段火箭的結構重量比，以增加入軌精度與酬載能力。混合式火箭引擎具相對安全、綠色環保、可推力控制、管路簡單、低成本等優點，並且可以輕易地達到引擎深度節流推力控制，對於僅能單次使用、需要精準進入軌道的入軌段火箭推進系統有相當大的應用潛力。其最大的優點是燃料在常溫下為固態、易保存且安全，即使燃燒室或儲存槽受損，固態的燃料也不會因此產生劇烈的燃燒而導致爆炸。雖然混合式推進系統有不少優於固態及液態推進系統的特性，相較事先預混燃料與氧化劑的固態推進系統及可精準控制氧燃比而達到高度燃燒效率的液態推進系統，混

合式推進系統有擴散焰邊界層燃燒特性，此因素導致混合式推進系統的燃料燃燒速率普遍偏低，使得設計大推力引擎設計時需要長度較長的燃燒室來提供足夠的燃料燃燒表面積，也導致得更高長徑比的火箭設計。針對此問題，本論文利用渦漩注入氧化劑的方式，增加了氧化劑在引擎內部的滯留時間，並藉由渦旋流場提升氧化劑與燃料的混合效率以及燃料耗蝕率；同時降低引擎燃燒室工作壓力以研究其推進效能，並與較高工作壓力進行比較。本論文使用氮氣加壓供流系統驅動90%高濃度過氧化氫 (high-test peroxide) 進入觸媒床，並使用三氧化二鋁 (Al2O3) 為載體的三氧化二錳 (Mn2O3) 觸媒進行催化分解，隨後以渦漩注入的

方式注入燃燒腔，並與燃料聚丙烯（polypropylene, PP）進行燃燒，最後經由石墨鐘形噴嘴 (bell-shaped nozzle) 噴出燃燒腔後產生推力。實驗部分首先透過深度節流測試先針對原版腔壓40 barA引擎在低腔壓下的氧燃比 (O/F ratio)、特徵速度 (C*)、比衝值 (Isp) 等引擎性能進行研究，提供後續設計20 barA低腔壓引擎的依據，並整理出觸媒床等壓損以及燃燒室等流速的引擎設計轉換模型；同時使用CFD模擬驗證渦漩注射器於氧化劑全流量下 (425 g/s) 的壓損與等壓損轉換模型預測的數值接近 (~1.3 bar)。由腔壓20 barA 引擎的8秒hot-f

ire實驗結果顯示，由於推力係數 (CF) 在低腔壓引擎的理論值 (~1.4) 相較於腔壓40 barA引擎的推力係數理論值 (~1.5) 較低，因此腔壓20 barA引擎的海平面Isp相較於腔壓40 barA引擎的Isp 低了約13 s，但是兩組引擎具有相近的Isp效率 (~94%)，且長時間的24秒hot-fire測試顯示Isp效率會因長時間燃燒而提升至97%。此外，氧化劑流量皆線性正比於推力與腔壓，判定係數 (R2) 也高於99%，實現混合式火箭引擎推力控制的優異性能。透過燃料耗蝕率與氧通量之關係式可知，低腔壓引擎在相同氧化劑通量下 (100 kg/m2s) 較腔壓40 barA引擎降低

了約15%的燃料耗蝕率，因此引擎的燃料耗蝕率會受到腔體壓力轉換的影響而變動，本論文也針對此現象歸納出一校正方法以預測不同腔壓下的燃料耗蝕率，此校正後的關係式可提供未來不同腔壓引擎燃料長度設計上的準則。最後將雙氧水貯存瓶的上游氮氣加壓壓力從約58 barA降低至38 barA並進行8秒hot-fire測試，結果顯示仍能得到與過往測試相當接近的Isp效率 (~94%)，而此特性除了能讓雙氧水及氮氣貯存瓶擁有輕量化設計的可能性，搭配具流量控制的控制閥也有利於未來箭體朝向blowdown type型式的設計，因此雙氧水加壓桶槽上的氮氣調壓閥 (N2 pressure regulator valve)

將可省去，得以降低供流系統的重量，並增加箭體的酬載能力，對於未來箭體輕量化將是一大優勢。

Avro Vulcan B Mk2: 1955-2015

為了解決Aerodynamic的問題，作者 這樣論述：

In 1955, the Vulcan B.Mk2 was proposed and a new wing modification was designed to take advantage of the more powerful Olympus engines and a new stand-off missile known as Blue Steel. The new wing was known as the Phase 2C development. Avro were given a contract for an aerodynamic prototype on 10

July 1956, with the first prototype VX777 making its first flight with the new wing on 31 August 1957. This led to a number of significant changes to the B.Mk2 electrical systems, flying controls and structure. The Avro Vulcan was originally designed as a high-altitude medium bomber, but the operat

ing requirement changed when it was required to fly at a low level. Thanks to the Vulcan’s inherently low aspect wing and structure, it proved more suitable to this role than the high aspect wings of the Vickers Valliant and Handley Page Victor.

通過使用流動分離控制改進翼型表面改性的數值模擬以提高氣動性能

為了解決Aerodynamic的問題，作者Andrew Gare Zebua 這樣論述：

One of the most widespread forms of alternative energy generation is the use of wind turbines. Wind turbines that use horizontal axis (HAWT) and wind turbines that use vertical axis(VAWT) are the two primary varieties of wind turbines that are put into operation today. One of the airfoils commonly

used as blades for VAWT is the DU 06 W 200. In order to increase aerodynamic performance and efficiency, it is crucial to control the flow separation and to know the fluid mechanics behavior of an airfoil. This thesis uses four methods to control flow separation on an airfoil: riblets, cavities, spo

ilers, and hybrid airfoils. Fluid mechanics that uses numerical equations has been used throughout the length of this thesis in order to explore and keep track of each unique example. This has been done in order to support the overall argument. Furthermore, the RANS equation K-Omega SST turbulence m

odel was adopted so that the findings would correctly reflect the turbulence flow that happens in the natural world. From the four methods mentioned, ten airfoil variants, including the base airfoil, have been conducted in this study. Even though the maximum CL to CD ratio of the riblets, cavity, an

d spoiler methods is lower than the plain airfoil, at some angles, the CL to CD ratio value is higher than the plain airfoil. After testing ten airfoil variants using five meters per seconds velocities, five of the best airfoil variants were chosen to be tested using different Reynolds numbers. In c

onclusion, it is decided if the hybrid airfoil method, especially hybrid blade airfoil 1, is the best because it could improve aerodynamic performance and delay the stall angle.