Download or read book Transonic Wind tunnel Investigation of Nozzle Hinge Moments for a Large Ballistic Missile Having Two Gimbaled Rocket Motors written by and published by . This book was released on 1959 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of Nozzle Hinge Moments on Two Launch Vehicle Models at Mach Numbers 1 60 2 00 and 2 40 written by and published by . This book was released on 1964 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Technique for Firing Dynamically Scaled Missile Models in Wind Tunnels and for Measuring Rocket motor Sound and Pressure Fluctuations written by William J. Alford and published by . This book was released on 1960 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Tests of Seven Static pressure Probes at Transonic Speeds written by Francis J. Capone and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel tests have been conducted to determine the errors of 3 seven static-pressure probes mounted very close to the nose of a body of revolution simulating a missile forebody. The tests were conducted at Mach numbers from 0.80 to 1.08 and at angles of attack from -1.7° to 8.4°. The test Reynolds number per foot varied from 3.35 x 106 to 4.05 x 106. For three 4-vane, gimbaled probes, the static-pressure errors remained constant throughout the test angle-of-attack range for all Mach numbers except 1.02. For two single-vane, self-rotating probes having two orifices at ±37.5° from the plane of symmetry on the lower surface of the probe body, the static-pressure error varied as much as 1.5 percent of free-stream static pressure through the test angle-of-attack range for all Mach numbers. For two fixed, cone-cylinder probes of short length and large diameter, the static-pressure error varied over the test angle-of-attack range at constant Mach numbers as much as 8 to 10 percent of free-stream static pressure.
Download or read book Transonic Aerodynamic Nozzle Hinge Moments of F 1 Engine Without Internal Flow on a Model of the S 1C Stage of Saturn 5 written by and published by . This book was released on 1965 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of Transonic Wind Tunnel Investigation to Determine the Effects of Nozzle Geomatry and Jet Plume on the Aerodynamics of a Body of Revolution Technical Report written by James H. Henderson and published by . This book was released on 1972 with total page 235 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Mach Numbers from 1 90 to 2 86 of a Canard controlled Missile with Ram air jet Spoiler Roll Control written by A. B. Blair and published by . This book was released on 1978 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of a Transonic Wind Tunnel Investigation of Thrust Effects on the Aerodynamics of Four Longitudinally Supported Ringtail Missile Configurations written by J. H. Henderson and published by . This book was released on 1973 with total page 93 pages. Available in PDF, EPUB and Kindle. Book excerpt: D MISSILES, TUBE LAUNCHEDTransonic wind tunnel tests were conducted on a strut-supported model to determine thrust effects on four longitudinal strut supported ringtail configurations. The configurations were achieved by varying the distance between the nozzle exit plane and the ringtail. Thrust was simulated by cold air and was varied from 0 to 400 pounds. Of primary interest, was the effect of thrust level and longitudinal position of the nozzle exit plane on missile stability. For the thrust levels tested, a favorable effect on longitudinal stability was experienced on the configuration with the nozzle exit plane located at the ringtail leading edge. The test was conducted at the Calspan Corporation's 8 foot Transonic Wind Tunnel at Mach numbers ranging from 0.4 to 1.2. Angles of attack were from -5 degrees to +6 degrees at a sideslip angle of 0 degrees. Thrust, from 0 to 400 pounds, was the only varying parameter. (Author).
Download or read book A Technique for Firing Dynamically Scaled Missile Models in Wind Tunnels and for Measuring Rocket motor Sound and Pressure Fluctuations written by William J. Alford and published by . This book was released on 1960 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of the Rolling Moments on a Cruciform Winged Missile with Forward Lateral Controls at Supersonic Speeds written by L. J. Beecham and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation If a Missile with an Operational Mid body Turbojet Engine written by Lamar M. Auman and published by . This book was released on 1993 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Boattailed Afterbodies on Base Heating and Motor Aerodynamic Hinge Moments of a Rocket Missile written by Robert A. Wasko and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of a Transonic Wind Tunnel Investigation of Trust Effects on the Aerodynamics of the Longbow Missile Configuration written by J. H. Henderson and published by . This book was released on 1973 with total page 81 pages. Available in PDF, EPUB and Kindle. Book excerpt: ERODYNAMICS OF THE Longbow Missile Configuration. Technical rept., Henderson, J. H. ;RD-TR-73-18DA-1-M-262303-A-214*Antiradiation missiles, *Transonic characteristics, *Wind tunnel tests, *Thrust, Wind tunnel models, Bodies of revolution, Fins, Aerodynamic configurations, Air to surface missiles, Jets, Air, Angle of attack, Base pressure, Plumes*LONGBOW missilesTransonic wind tunnel tests were conducted on a strut-mounted model of the LONGBOW missile configuration to determine thrust effects on a body of revolution afterbody with fins located at various longitudinal positions. Thrust was simulated by a cold air axial jet. Base pressure and afterbody forces and moments were measured. The test was conducted at Mach numbers from 0.4 to 1.25 and at angles of attack from -2 degrees to 10 degrees. Jet thrust was varied from 0 to 400 pounds. Reynolds number per foot varied from 0.7 to 1.7 million. (Modified author abstract).
Download or read book Transonic Wind Tunnel Tests of a Base Drag Research Missile Model written by B. F. Gorin and published by . This book was released on 1970 with total page 583 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in order to obtain data describing the effects of various simulated rocket exhaust plumes on the model's external flow field. Data describing the flow in the nozzle exit plane and in the model boundary layer were also obtained. Model external static pressure measurements were made and Schlieren, shadowgraph and tuft photographs were taken. The tests were conducted at Mach numbers from 0.000 to 1.200 at angles of attack from -2 to +2 degrees. The report presents details of the test program, an outline of the test procedure and the results of the investigation in tabular form. (Author).
Download or read book Wind tunnel Investigation at Mach Numbers from 0 40 to 1 20 of the Static Aerodynamic and Control Characteristics of a Model of a Nonlifting Reeintry Capsule in Combination with a Rocket Booster written by Albin O. Pearson and published by . This book was released on 1960 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Supersonic Speeds of a Canard controlled Missile with Fixed and Free rolling Tail Fins written by A. B. Blair and published by . This book was released on 1978 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Preliminary Low Speed Wind Tunnel Investigation of Some Aspects of the Aerodynamic Problems Associated with Missiles Carried Externally in Positions N written by U. S. Government Printing Office and published by BiblioGov. This book was released on 2013-07 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be traversed by the missiles showed abrupt gradients in both flow angularity and in local dynamic pressure. Through the use of aerodynamic data on the isolated missile and the measured flow-field characteristics, the longitudinal forces and moments acting on the missile while in the presence of the wing-fuselage combination could be estimated with fair accuracy. Although the lateral forces and moments predicted were qualitatively correct, there existed some large discrepancies in absolute magnitude.
