本文選題：飛機結(jié)冰 + 數(shù)值模擬　； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：飛機在飛行過程中遇到特定氣象條件時,會發(fā)生結(jié)冰并改變原來的外形,從而對其氣動特性、操縱性以及穩(wěn)定性等造成破壞,給飛行安全帶來隱患。實際的結(jié)冰是一個多學(xué)科綜合的復(fù)雜物理過程,對該過程進行數(shù)值模擬時需要建立相對應(yīng)良好的模型才能獲得較為準(zhǔn)確的結(jié)果。現(xiàn)階段國內(nèi)外大部分學(xué)者采用的都是基于Messinger思想的數(shù)值模型,這類模型普遍有著簡單、準(zhǔn)確、易于計算等優(yōu)勢,但是由于模型的連續(xù)性,使其在結(jié)冰的微觀現(xiàn)象捕捉方面有所不足。因此本文在考慮單個水滴離散運動的情況下,采用了一種基于Szilder思想的新模型來進行結(jié)冰預(yù)測數(shù)值模擬。文中的主要工作有:(1)采用高效的CFD軟件Fluent對機翼繞流流場進行模擬,并將計算所得的機翼表面壓力系數(shù)與相關(guān)試驗數(shù)據(jù)進行了對比,說明了該方法的可行性。(2)為了考察數(shù)值模擬冰形在研究結(jié)冰對機翼氣動特性影響中的有效性,對一組試驗冰形和基于Messinger模型的數(shù)值模擬冰形在ICEM中進行了結(jié)構(gòu)化網(wǎng)格劃分,并在Fluent中分別進行了兩種冰形在不同攻角情況下的升阻力系數(shù)計算,通過對結(jié)果的分析說明了數(shù)值模擬冰形在計算結(jié)冰后的機翼氣動特性時存在一定的誤差。(3)利用歐拉法建立了水滴運動特性的控制方程,進行了幾組不同直徑下的水滴撞擊特性的計算,得到了結(jié)冰機翼表面的水滴收集系數(shù),為結(jié)冰預(yù)測提供了初始條件。(4)基于一種新的思想建立了隨機結(jié)冰模型,其中包括水滴的隨機發(fā)射模型、隨機運動模型以及結(jié)冰概率模型。編寫了模擬結(jié)冰的程序,并對不同條件下的結(jié)冰進行了數(shù)值預(yù)測,最后將模擬冰形與試驗值以及基于Messinger模型的CIRAMIL的計算結(jié)果進行了對比,并對隨機結(jié)冰模型的優(yōu)劣提出了評價。
[Abstract]:In the course of flight, the aircraft will freeze and change its original shape, which will destroy its aerodynamic characteristics, maneuverability and stability, and bring hidden trouble to flight safety. The actual icing is a complex physical process which is synthesized by many subjects. In order to obtain more accurate results, a good corresponding model is needed for numerical simulation of the process. At present, most scholars at home and abroad adopt numerical models based on Messinger thought. These models generally have the advantages of simple, accurate and easy to calculate, but because of the continuity of the model, It is insufficient in catching the microscopic phenomenon of ice formation. In this paper, a new model based on Szilder is used to simulate the ice formation in the case of discrete motion of single water droplet. The main work in this paper is: (1) the flow field around the wing is simulated by using the efficient CFD software Fluent, and the calculated surface pressure coefficient of the wing is compared with the experimental data. The feasibility of this method is illustrated. In order to investigate the effectiveness of numerical simulation ice shape in studying the effect of icing on the aerodynamic characteristics of wing, a group of experimental ice shapes and numerical simulation ice shapes based on Messinger model are divided into structured meshes in ICEM. The lifting resistance coefficient of two ice shapes at different angles of attack is calculated in Fluent. The analysis of the results shows that there is a certain error in the calculation of the aerodynamic characteristics of the frozen wing in the numerical simulation of the ice shape. The Euler method is used to establish the governing equation of the motion characteristics of the water droplets. In this paper, several groups of water droplets with different diameters are calculated, and the water droplet collection coefficients on the surface of the frozen wing are obtained. The initial conditions for ice prediction are provided. (4) based on a new idea, a stochastic icing model is established. These models include the random emission model of water droplets, the random motion model and the icing probability model. The program of simulating icing is compiled, and the ice formation under different conditions is predicted numerically. At last, the simulated ice shape is compared with the experimental data and the calculated results of CIRAMIL based on Messinger model, and the merits and demerits of stochastic icing model are evaluated.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V321.229

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