高扬程机翼设计 A short take-off and landing (STOL) aircraft must be able to fly at low controlled speeds, yet it must also offer acceptable cross-country (cruise) performance. 一个简短的起飞和着陆（短距起降）飞机必须能够控制飞行速度低，但它也必须接受上述报价越野（巡航）的性能。 The challenge is to design a wing with a high lift coefficient so that the wing area is as small as possible, while allowing for take-off and landing speeds that are as low as possible. 目前的挑战是设计一个可能的机翼升力系数与高，使机翼面积为小，同时允许起飞和降落速度是尽可能低。 Short wings make the aircraft easier to taxi, especially when operating in an off-airport environment with obstructions. 短翼飞机更容易使出租车，尤其是当障碍物经营机场的环境与场外。 They also allow for better visibility, and require less space for hangaring, while also being easier to build and stronger (less weight and wing span to support). 他们还允许更好的知名度，并需要更少的hangaring空间，但同时也更容易建立和更强（重量轻和翼展支持）。 The STOL CH 801 uses a special airfoil design to achieve very high lift, low stall speeds, and high strength. 甲烷的短距起落801使用一个特殊的翼型设计，达到非常高扬程，低失速速度，强度高。 A thick wing, full-length leading-edge slats and trailing edge 'junker' type flaperons develop a maximum wing lift coefficient of 3.10, while maintaining a short wing-span – for maximum strength and ground maneuverability. 厚厚的机翼，全长领先的缝翼和后缘'勇克'型襟副翼发展的最大机翼升力系数3.10，同时保持一个短翼跨度-最大强度和地面可操作性。
The stall of the wing occurs at the highest lift coefficient on an airfoil, when the airflow can no longer go around the airfoil's nose (leading edge) and separates from the upper wing surface. 机翼失速的发生在电梯表面系数最高的机翼上，当气流不能继续围绕翼型的鼻子（领先），并脱离机翼上。 Conventional trailing-edge wing flaps help delay the stall to a higher lift coefficient, but only with limited effectiveness. However, by combining the use of trailing-edge flaps with leading-edge slats, the wing's lift coefficient can be effectively doubled if used on the full span of the wing. 传统的后缘襟翼有助于延缓失速到一个更高的升力系数，但只有有限的成效。然而板条，结合边缘皮瓣与领先使用的后缘，机翼的升力系数，可有效地增加一倍，如果用在机翼完整的跨度。
Leading-Edge Wing Slats: 前沿翼板条： What Are They and How Do They Work? 什么是他们和他们如何工作？
![]() The leading edge slats allow the aircraft to fly at a high angle of attack (lower speed) by accelerating the air between the slat and the wing (venturi effect). 在前缘缝翼使飞机）飞在低速高攻角（加速效果）空气之间的缝翼和翼（文丘里。 The leading edge slats allow for steep climb angles of up to 30-degrees. 在前缘缝翼允许30度角的陡坡攀登到。 For maximum reliability and to keep construction simple, the leading edge slats are engineered to remain in a fixed position in all flight attitudes, and do not retract (in level flight, the fixed leading edge slats have minimal effect on cruise). 为了获得最大的可靠性，并保持施工简单，前缘缝翼的设计能够留在飞行中的所有固定位置的态度，不要收回（在水平飞行时，前缘缝翼有固定的邮轮影响最小）。 The full-length flaperons act as both full-span ailerons and full-span flaps. 全长的襟副翼同时扮演全跨度副翼和全跨度皮瓣。 The flaperons have their own airfoil, and are hung below the wing trailing edge to supply them with fresh undisturbed air for maximum control effectiveness even at low speeds. 襟副翼有自己的翼型，并挂在机翼后缘下方新鲜空气原状的速度控制在较低的最大效益，甚至他们与供应。 |
Leading edge slats prevent the stall up to approximately 30 degrees incidence (angle of attack) by picking up a lot of air from below, where the slot is large and accelerating the air in the funnel shaped slot (venturi effect) and blowing this fast air tangentially on the upper wing surface through the much smaller slot. 前缘缝翼防止失速高达约30度的发病率（攻角）拿起空气，从下面很多地方槽大，加速空气中的漏斗形槽（文丘里效应），空气吹这个快速发展切，通过对上翼面小得多插槽。 This effectively "pulls" the air around the leading edge, thus preventing the stall up to a much higher angle of incidence and lift coefficient. 这将有效地“拉”前沿周围的空气，从而防止失速到一个更高的入射角和升力系数。
The disadvantage of leading-edge slats is that the air acceleration in the slot requires energy (it creates additional drag). 板条不利的领先优势是，在槽中的空气加速需要能量（它创造更多的阻力）。 While many STOL designs utilize retractable leading-edge slat devices, the additional weight, complexity, reliability issues and cost of such systems minimize their feasibility for use in light aircraft and their overall effectiveness. 虽然许多短距起落伸缩设计利用最先进的板式设备，额外的重量，复杂性，可靠性问题和系统的成本效益等最大限度地减少其使用的可行性整体轻型飞机及对策。
At the wing tip, the STOL CH 801 design utilizes 'Hoerner' tips to maximize the wing's effective lift area and to minimize wing tips vortices. 在翼尖，甲烷的短距起降801的设计，采用'霍纳'提示，最大限度地机翼的有效面积，并尽量减少电梯提示旋涡翼。 Hoerner wing tips provide the largest effective span for a given geometric span or a given wing weight. 霍纳翼尖翼提供给定的重量最大有效跨度为给定的几何大跨度或。 | ![]() |
The wings are braced by dual steel wing struts, and are bolted to the fuselage at the cabin frame with four bolts for easy wing attachment and removal. 翅膀是支撑钢翼双支柱，并固定在去除附着在机身和机翼的客舱与四架螺栓容易。
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STOL CH 801: Designed for superior visibility 短距起落甲烷801：专为卓越的可视性 ABOVE-CAB WINGS : The aircraft wings are positioned above the cabin and fuselage - this allows for excellent horizontal visibility as the wings are located above the pilot's head to provide pilot and passenger with superior visibility. 以上的CAB翼 ：飞机机翼上方的位置舱和机身-这使得优秀的水平能见度为机翼上方的能见度飞行员的脑袋，乘客和驾驶员提供优越。 In addition, the wings taper at the wing root to meet the 'skylight' top window – maximizing upward visibility, a feature especially useful in steep turns. 此外，翼翅锥度的根，以满足天窗的顶级窗口-最大化向上的知名度，变成有用的功能，特别是在陡峭。 While providing great visibility, the 'above-cab' wing design minimizes the frontal area of the aircraft to reduce drag, while also allowing the airflow to travel undisturbed from the propeller to the tail sections – further maximizing slow flight control of the aircraft. 在提供巨大知名度，'上面驾驶室翼设计最大限度地减少飞机的迎风面积，以减少阻力，同时也使螺旋桨气流不受干扰旅行从到尾部分-进一步延长了飞机的飞行控制缓慢。 | 
发表于 2010-10-24 11:00
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