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超音速流通過F-16機翼釋放飛彈高度變化數值探討 = = Numeric...

陳信竹

超音速流通過F-16機翼釋放飛彈高度變化數值探討 = = Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation /

紀錄類型:	書目-語言資料,印刷品 : Monograph/item
正題名/作者:	超音速流通過F-16機翼釋放飛彈高度變化數值探討 =/ 陳信竹.
其他題名:	Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation /
其他題名:	Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation.
作者:	陳信竹
出版者:	雲林縣 :國立虎尾科技大學 , : 民113.07.,
面頁冊數:	[10], 94面 :圖, 表 ; : 30公分.;
附註:	指導教授: 楊世英.
標題:	thrust. -
電子資源:	電子資源

超音速流通過F-16機翼釋放飛彈高度變化數值探討 = = Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation /
陳信竹

超音速流通過F-16機翼釋放飛彈高度變化數值探討 =Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation /Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation.陳信竹. - 初版. - 雲林縣 :國立虎尾科技大學 ,民113.07. - [10], 94面 :圖, 表 ;30公分.

指導教授: 楊世英.

碩士論文--國立虎尾科技大學飛機工程系航空與電子科技碩士班.

含參考書目.

本文採用商用軟體ESI CFD來研究超音速流通過F-16機翼釋放飛彈高度變化數值模擬，在卡式座標系統下求解6-DOF剛體運動方程式和三維非穩態Euler方程式，使用重疊型網格(Chimera Grid)系統，讓不同區塊流場網格資料分別計算，而重疊區的格點訊息相互運算。將機翼流場與彈體流場結合，分析6-DOF剛體運動方程式取得計算結果，將彈體重心、速度、翻滾角度、角速度計算結果與實驗值進行比對，計算結果趨勢相近，再來使用不同高度的條件，進行機翼釋放彈體數值模擬。機翼分別在1000公尺、6000公尺、11600公尺處釋放彈體，探討機翼分離彈體的軌跡。隨著高度增加並施加8G推力釋放飛彈時，X軸方向，向前偏移量會逐漸增加；Y軸方向，向翼尖偏移量最小值逐漸變大；Z軸方向下位移量逐漸減少。.

(平裝)Subjects--Topical Terms:

1420413
thrust.

超音速流通過F-16機翼釋放飛彈高度變化數值探討 = = Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation /
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245 1 0 $a 超音速流通過F-16機翼釋放飛彈高度變化數值探討 = $b Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation / $c 陳信竹.
246 1 1 $a Numerical Investigation of Supersonic Flows over a Missile Released from F-16 Wing with Altitude Variation.
250 $a 初版.
260 # $a 雲林縣 : $b 國立虎尾科技大學 , $c 民113.07.
300 $a [10], 94面 : $b 圖, 表 ; $c 30公分.
500 $a 指導教授: 楊世英.
500 $a 學年度: 112.
502 $a 碩士論文--國立虎尾科技大學飛機工程系航空與電子科技碩士班.
504 $a 含參考書目.
520 3 $a 本文採用商用軟體ESI CFD來研究超音速流通過F-16機翼釋放飛彈高度變化數值模擬，在卡式座標系統下求解6-DOF剛體運動方程式和三維非穩態Euler方程式，使用重疊型網格(Chimera Grid)系統，讓不同區塊流場網格資料分別計算，而重疊區的格點訊息相互運算。將機翼流場與彈體流場結合，分析6-DOF剛體運動方程式取得計算結果，將彈體重心、速度、翻滾角度、角速度計算結果與實驗值進行比對，計算結果趨勢相近，再來使用不同高度的條件，進行機翼釋放彈體數值模擬。機翼分別在1000公尺、6000公尺、11600公尺處釋放彈體，探討機翼分離彈體的軌跡。隨著高度增加並施加8G推力釋放飛彈時，X軸方向，向前偏移量會逐漸增加；Y軸方向，向翼尖偏移量最小值逐漸變大；Z軸方向下位移量逐漸減少。.
520 3 $a In this thesis, the commercial software ESI CFD FASTRAN is used to study the supersonic flows over a missile released from F-16 wing with altitude variation and 8G thrust. Three-dimensional unsteady Euler equations and six degree of freedom (6-DOF) rigid body motion equations are solved in the Cartesian coordinate. The Chimera grid system is used and the information of multiple blocks is calculated separately. Grid communication among multiple blocks is automatically implemented to obtain calculated results by coupling flow fields between a store and a wing and 6-DOF rigid-body motion equation. To evaluate the accuracy of the present calculation, the calculated store instantaneous trajectory of center of gravity of store, velocity, angles of roll and angular rate are compared with those of experimental data. The results are in good agreement with the experimental data. Store separation at 1000m, 6000m and 11600m is employed to investigate the trajectory of a store. In addition, the 8G thrust is added to analyze the physical variation of the store. As the altitude increases and an 8G thrust is applied when releasing the missile, the forward displacement in the X-axis gradually increases; in the Y-axis, the minimum wingtip displacement gradually increases; in the Z-axis, the downward displacement gradually decreases..
563 $a (平裝)
650 # 4 $a thrust. $3 1420413
650 # 4 $a altitude. $3 1346250
650 # 4 $a F-16 wing. $3 1450779
650 # 4 $a missile. $3 1218056
650 # 4 $a supersonic. $3 1218055
650 # 4 $a 推力. $3 1420412
650 # 4 $a 高度. $3 1346249
650 # 4 $a F-16機翼. $3 1450778
650 # 4 $a 飛彈. $3 995589
650 # 4 $a 超音速. $3 1218053
856 7 # $u https://handle.ncl.edu.tw/11296/7eyc8r $z 電子資源 $2 http