Download or read book Wind Tunnel Investigation to Determine Static Stability and Pressure Distribution Characteristics of Small scale Models of the Titan Iii mol Launch Configuration at Mach Numbers from 0 60 to 3 10 written by and published by . This book was released on 1966 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Models of the Titan 3 Manned Orbiting Laboratory (MOL) launch vehicle were tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility at Mach numbers from 0.60 to 3.10 to determine pressure and acoustical characteristics for structural design confirmation and to obtain force balance data for flight control and trajectory analysis. A calibration cone was also tested to evaluate tunnel background noise in the Titan 3 MOL acoustical data. Force data were obtained by using four internal balances to sense separate aerodynamic loads on the composite model and on the MOL, MOL-Gemini, and solid rocket motors (SRM) sections. Modification of the SRM noses to a less blunt configuration resulted in a reduction of composite and SRM axial load and tended to position the composite longitudinal neutral point at a more forward location. Lateral neutral point for the composite model exhibited a maximum travel of 2.6 core diameters for the 0.60 and 3.10 Mach number range whereas the longitudinal neutral-point travel was 1.0 diameters. The acoustical results are not presented in this report. (Author).
Download or read book Wind Tunnel Investigation to Determine Pressure Distribution Characteristics of a 0 03 scale Model of the Titan Iii mol Launch Configuration During the Abort Sequence at Mach Numbers from 0 60 to 3 00 written by D. A MacLanahan (Jr) and published by . This book was released on 1967 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 0.03-scale model of the Titan III/Manned Orbiting Laboratory (MOL) launch vehicle was tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility at Mach numbers from 0.6 to 3.0 to determine pressure distributions on the airborne vehicle during the abort sequence. Test results show that the jet, simulating thrust termination, forces the solid-propellant motor induced normal shock forward. Disturbances caused by the jet produce an increase in the pressure coefficient in the region ahead of the jet and a decrease in the pressure coefficient in the region aft of the jet.
Download or read book Wind Tunnel Investigation to Determine Aerodynamic Characteristics of a 0 03 scale Model of the Titan Iii mol Launch Configuration During the Abort Sequence at Mach Numbers from 0 60 to 3 00 written by M. L. Homan and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 0.03-scale model of the Titan III/Manned Orbiting Laboratory (MOL) launch vehicle was tested in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility at Mach numbers from 0.6 to 3.0 to obtain aerodynamic force and moment data on the airborne vehicle during the abort sequence. Test results show that there was a reduction in magnitude of the pitching-moment and normal-force coefficients at all angles of attack as jet pressure ratio was increased. Thrust termination (jet off to jet on) resulted in an increase in the magnitude of both the yawing-moment and side-force coefficients at all angles of attack. (Author).
Download or read book WIND TUNNEL STUDY OF THE EFFECT OF MOL PROTUBERANCES ON STATIC STABILITY AND PRESSURE DISTRIBUTION CHARACTERISTICS FOR SMALL SCALE MODELS OF THE TITAN III MOL LAUNCH VEHICLE written by and published by . This book was released on 1967 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: Force, pressure, and acoustical data were obtained for the Titan III/ MOL (Manned Orbiting Laboratory) launch vehicle in Tunnels 16T and 16S of the Propulsion Wind Tunnel Facility. The primary objective of the test was to determine the effect of MOL protuberances on stability and axial-force coefficients and on surface pressure distributions. The force data were measured using three balances which sensed aerodynamic loads separately on the MOL-Gemini section, on the composition vehicle, and on one solid rocket motor. Mach number was varied from 0.60 to 3.00. Protuberance variations produced measurable changes in stability and axial-force characteristics for the MOL-Gemini section only. Surface pressures near the protuberances returned to protuberance-free trends within approximately 0.5-core diameters downstream of a protuberance trailing edge.
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 812 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Mach Numbers from 3 0 to 6 8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations written by Albin O. Pearson and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of the Buffet Characteristics of Truncated 0 079 scale Models of the Titan III and Titan IV Launch Vehicles at Mach Numbers from 0 60 to 1 60 written by J. A. Black and published by . This book was released on 1988 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at a Mach Number of 2 91 of Stability and Control Characteristics of Three Lifting Reentry Configurations at Angles of Attack Up to 90 written by John E. Grimaud and published by . This book was released on 1961 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Characteristics of Major Active Wind Tunnels at the Langley Research Center written by William T. Schaefer and published by . This book was released on 1965 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains a brief description of each of the major active wind tunnels at the Langley Research Center.
Download or read book Wind Tunnel Tests of Rectangular Finned Variable Gap Tangent Ogive cylinder Model at Mach Numbers 1 75 to 4 50 written by Neil Arthur Zarin and published by . This book was released on 1964 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Mach Numbers from 3 0 to 6 8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations written by and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Large scale Wind tunnel Investigation of an M1 L Lifting Body with an Inflatable and a Rigid Afterbody written by Kenneth W. Mort and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of Three Axisymmetric Cowls of Different Lengths at Mach Numbers from 0 60 to 0 92 written by Richard J. Re and published by . This book was released on 1993 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Pressure Measurements in the Wake of a Cone cylinder Model at Mach Numbers of 2 30 and 4 65 written by John T. McShera and published by . This book was released on 1965 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Mach Numbers from 1 60 to 4 50 of the Static stability Characteristics of Two Nonlifting Vehicles Suitable for Reentry written by Kenneth L. Turner and published by . This book was released on 1959 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Measurements of Aerodynamic Damping Derivatives of a Launch Vehicle Vibrating in Free free Bending Modes at Mach Numbers from 0 70 to 2 87 and Comparisons with Theory written by Perry W. Hanson and published by . This book was released on 1962 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of Three Proposed Launch Vehicles at Mach Numbers from 2 30 to 4 63 written by A. B. Blair and published by . This book was released on 1968 with total page 65 pages. Available in PDF, EPUB and Kindle. Book excerpt:
