Effect of Unsymmetrical Nose-Bluntness of the Pressure Distribution Over a 10 Degree Cone at Mach-14 PDF Download
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Author: Otto Walchner Publisher: ISBN: Category : Languages : en Pages : 46
Book Description
The pressure distribution over a 10 deg cone was measured in ARL's 20-inch hypersonic wind tunnel at Mach-14 and for various angles of attack and sideslip. The effect of different unsymmetrically blunted noses, with small bluntness ratios, on the pressure distribution is investigated. Test results relate any small unsymmetrical nose bluntness to the rotational symmetry of the flow over a body of revolution at high Mach numbers. The reported test complement, AD-711 921. (Author).
Author: Otto Walchner Publisher: ISBN: Category : Languages : en Pages : 46
Book Description
The pressure distribution over a 10 deg cone was measured in ARL's 20-inch hypersonic wind tunnel at Mach-14 and for various angles of attack and sideslip. The effect of different unsymmetrically blunted noses, with small bluntness ratios, on the pressure distribution is investigated. Test results relate any small unsymmetrical nose bluntness to the rotational symmetry of the flow over a body of revolution at high Mach numbers. The reported test complement, AD-711 921. (Author).
Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 738
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Otto Walchner Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 0
Book Description
In the analysis of the free flight motion of bodies of revolution, the tricyclic theory assumes that a small configurational asymmetry does not violate the rotational symmetry of the stability derivatives in pitch and yaw but does produce a non-zero trim angle. Tests at Mach 14 show that a small unsymmetric nose bluntness destroys the rotational symmetry of the stability derivatives of a slender cone at hypersonic Mach numbers and therefore severely violates the assumptions of the tricyclic theory. Restoring and damping derivatives in pitch and yaw are reported for a 10 deg cone with symmetric and unsymmetrically blunted noses. The effect of non-equal stability derivatives on the motion are shown for a simplified case. (Author).
Author: Otto Walchner
Author: Otto Walchner
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Author: Otto Walchner
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Author: Hypersonic Research Laboratory (U.S.)
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