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Investigation of interference lift, drag, and pitching moment of a series of triangular-wing and body combinations at a Mach number of 1.94

Description: Report presenting an investigation at Mach number 1.94 of a series of triangular-wing and body combinations to determine the interference lift, drag, and pitching moment. The models had a series of seven flat-plate triangular wings of varying scale, four with semiapex angles of 30 degrees, and three with semiapex angles of 45 degrees. Results indicated that the interference between the wing and the body gave an increase in lift over the wing and body alone, but at the expense of more drag.
Date: December 21, 1955
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Investigation of interference, lift, drag, and pitching moment of a series of rectangular wing and body combinations at Mach numbers of 1.62, 1.93,and 2.41

Description: Report presenting an investigation of a series of rectangular wing and body combinations at Mach numbers 1.62, 1.93, and 2.41 to determine the effects of aspect ratio, incidence angle, and forebody length on the interference lift, drag, and pitching moment. A limited investigation to determine the effect of Reynolds number on the wings in the presence of the body was also carried out. Information regarding wing lift, basic quantities for interference evaluation, interference qualities, contributions of the various components, and the concept of wing-lift carry-over is provided.
Date: August 13, 1952
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel

Description: Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.
Date: December 19, 1952
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Measurements and predictions of flow conditions on a two-dimensional base separating a Mach number 3.36 jet and a Mach number 1.55 outer stream

Description: Report presenting an investigation in a mixing-zone apparatus to determine the effects of jet flow on two-dimensional base pressure and the development of supersonic channel flow about a two-dimensional base, with and without splitter plates of different thicknesses. Results regarding the starting cycle for outer streams only, the fully established supersonic flow, and the base pressure between the center jet and outer streams are provided.
Date: May 7, 1954
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the forces and moments due to sideslip of a series of triangular vertical- and horizontal-tail combinations at Mach numbers of 1.62, 1.93, and 2.41

Description: Report presenting an experimental investigation at three Mach numbers of a series of tail combinations consisting of a triangular vertical tail attached symmetrically to a triangular horizontal tail to determine the lateral force, yawing moment, and rolling moment due to sideslip. The results indicated that the lateral-force derivative and yawing-moment derivative were predicted satisfactorily with the method used with the exception of when leading edges approach a sonic condition.
Date: March 1957
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Investigation of two pitot-static tubes at supersonic speeds

Description: The results of tests at a Mach number of 1.94 of an ogives-nose cylindrical pitot-static tube and similar tests at Mach numbers of 1.93 and 1.62 of a service pitot-static tube to determine body static pressures and indicated Mach numbers are presented and discussed. The radial pressure distribution on the cylindrical bodies is compared with that calculated by an approximate theory.
Date: November 19, 1948
Creator: Hasel, Lowell E. & Coletti, Donald E.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of a Number of Total Pressure Tubes at High Angles of Attack

Description: Report presenting a wind-tunnel investigation to determine the effect of inclination of the air stream on the measured pressures of 20 total-pressure tubes through a range of angles of attack and Mach numbers. Generally, the range of angle of attack over which the tubes remained insensitive to inclination was appreciably greater at supersonic speeds than at subsonic speeds.
Date: January 1951
Creator: Gracey, William; Coletti, Donald E. & Russell, Walter R.
Partner: UNT Libraries Government Documents Department