An Experimental Study on the Oil Film Method and Pressure of a Missile Body at High-angle-of Attack with Lateral Jet

• Main Authors: Wen-Bin Chio, 邱文彬
• Other Authors: Jiun-Jih Miau
• Format: Others
• Language: zh-TW
• Published: 2000
• Online Access: http://ndltd.ncl.edu.tw/handle/27477166748145994979

碩士 === 國立成功大學 === 航空太空工程學系 === 88 === The purpose of the study is to investigate the tangent ogive forebody fineness ratio of 2 at high angle of attack tested in transonic regime. The Mach numbers performed in wind tunnel are 0.3, 0.6, 0.78 and 0.86, respectively, and the corresponding Reynolds numbers, based on the diameter of missile, are 、 、 and , respectively. The angle of attacks chosen in the experiments are and , respectively. The experiments were conducted in a 600mm 600mm transonic wind tunnel located at the Aerospace Science and Technology Research Center of National Cheng-Kung University. Results show that laminar、transitional、turbulent and secondary separation may occur in the body surface. Flow separation could also be induced by shock at angle-of-attack in the range of at M=0.78 and higher. With the increase of Mach number, the magnitude of boundary layer separation gets symmetric hence the side force is reduced. As the pressure variations due to the jet issuing from the leeward side are concerned, the effect gets more prominent at low angle of attack than at high angle of attack. Also noted, the effect of the jet reduced as Mach number gets increase at high angle of attack.