Experimental Investigation of Aerodynamics over Transonic Missile Body with Lateral Jet

• Main Authors: Chih-Hua Lin, 林志華
• Other Authors: Jiun-Jih Miau
• Format: Others
• Language: zh-TW
• Published: 2001
• Online Access: http://ndltd.ncl.edu.tw/handle/56740491166035717625

碩士 === 國立成功大學 === 航空太空工程學系 === 89 === An experimental investigation was conducted in transonic wind tunnel for studying the aerodynamics characteristics due to a lateral jet from an ogive nose missile body having a fineness ratio of 2. The test Mach numbers range from 0.3 to 0.86, the corresponding Reynolds numbers, based on the diameter of the ogive cylinder are 0.45╳10^6 to 1.45╳10^6. The angle of attacks chosen in the experiments are -5~10 deg and 35~50deg. Dye injection method, colored schlieren method, oil film method and pressure measurements were employed to observe three-dimensional flow separation and shock formation at high angle of attack. In addition, a force balance was employed to determine the interaction between a lateral jet and the external flow at low angle of attack, then to reduce the amplification factor K. Pressure measurements show that laminar、turbulent and secondary separation are occurred on the missile body surface. From the schlieren photographs, the shock formation was revealed, induced at high angle of attack, in the range of 35~50 deg, when Mach number was larger than 0.78. Results from force measurements at low angle of attack show that K factor increases with increasing positive angle of attack, Mach number and jet mass flow rate. However when Mach number is 0.86, K factor decreases significantly due to shock-jet interaction. In addition, it is noted that the jet circumferential position can have a noticeable effect on the magnitude of jet force amplification.