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Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 070 To 084
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Book Synopsis Sting-support Interference on Longitudinal Aerodynamic Characteristics of Cargo-type Airplane Models at Mach 0.70 to 0.84 by : Donald L. Loving
Download or read book Sting-support Interference on Longitudinal Aerodynamic Characteristics of Cargo-type Airplane Models at Mach 0.70 to 0.84 written by Donald L. Loving and published by . This book was released on 1967 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Sting-support Interference on Longitudinal Aerodynamic Characteristics of Cargo-type Airplane Models at Mach 0.70 to 0.84 by : Donald L. Loving
Download or read book Sting-support Interference on Longitudinal Aerodynamic Characteristics of Cargo-type Airplane Models at Mach 0.70 to 0.84 written by Donald L. Loving and published by . This book was released on 1967 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Subsonic Sting Interference on the Aerodynamic Characteristics of a Family of Slanted-base Ogive-cylinders by : Colin P. Britcher
Download or read book Subsonic Sting Interference on the Aerodynamic Characteristics of a Family of Slanted-base Ogive-cylinders written by Colin P. Britcher and published by . This book was released on 1990 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Aeronautical Journal written by and published by . This book was released on 1990 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Interference on a Model Afterbody from Downstream Support Hardware at Transonic Mach Numbers by : Earl A. Price (Jr.)
Download or read book Interference on a Model Afterbody from Downstream Support Hardware at Transonic Mach Numbers written by Earl A. Price (Jr.) and published by . This book was released on 1981 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to parametrically study the interference on an afterbody model that would be produced by the aft-support blade used with a wingtip support system. Geometric variables included the blade axial location, thickness, span, chord, and leading- and trailing-edge contours. Data were obtained over the Mach number range from 0.6 to 1.2 with the model at zero angle of attack. Interference was evaluated by comparing afterbody drag from a reference configuration, which had the aft-support blade removed, to the various configurations with a blade installed. A reasonable correlation of the blade interference effects on the afterbody drag coefficient was obtained, which included the influence of support blade axial position and blockage. Decreasing blade leading-edge bluntness by a factor of two resulted in a significant reduction of interference in the Mach number range from 0.9 to 1.1. Significantly greater interference was measured without jet flow than with jet flow. It is shown that a Euler equation computer code is a useful tool for the design of minimum interference support systems. (Author).
Book Synopsis Influences of Sting Support on Aerodynamic Loads Acting on Captive Store Models by : R. E. Dix
Download or read book Influences of Sting Support on Aerodynamic Loads Acting on Captive Store Models written by R. E. Dix and published by . This book was released on 1976 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt: In a series of wind tunnel tests, measurements were made of the aerodynamic loads acting on eight different store configurations mounted in the external captive position on a one-twentieth-scale model of the F-4C aircraft. Store models included blunt and contoured afterbody shapes, stable and unstable designs, and large (one per pylon) and small (rack-mounted) configurations. The tests were conducted in an effort to evaluate sting effects on captive store loads. Sting effects were considered to consist of two contributions: the effect of altering the afterbody of a store to allow insertion of a sting, and the effect of the presence of the sting. Altering the afterbody of an unstable store influenced captive loads less than altering a stable configuration. It was also determined that the presence of a sting affected most the pitching and yawing moments.
Book Synopsis Hosmer's Interest and Discount Table by :
Download or read book Hosmer's Interest and Discount Table written by and published by . This book was released on 1839* with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Sting Support Interference on the Base Pressures of a Model Having a Blunt Nosed Cylinder Body and a Conical Flare at Mach Numbers of 0.65 to 2.20 by :
Download or read book Effects of Sting Support Interference on the Base Pressures of a Model Having a Blunt Nosed Cylinder Body and a Conical Flare at Mach Numbers of 0.65 to 2.20 written by and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effects of Static Margin and Rotational Damping in Pitch on the Longitudinal Stability Characteristics of an Airplane as Determined by Tests of a Model in the NACA Free-flight Tunnel by : John P. Campbell
Download or read book The Effects of Static Margin and Rotational Damping in Pitch on the Longitudinal Stability Characteristics of an Airplane as Determined by Tests of a Model in the NACA Free-flight Tunnel written by John P. Campbell and published by . This book was released on 1944 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rotational damping in pitch was varied over a wide range by using horizontal tails that varied in area from 0 to 24 percent of the wing area. A range of static margins from 2 to 16 percent of the mean aerodynamic chord was covered in the tests. For each test condition the model was flown and the longitudinal steadiness characteristics were noted. It was found in the investigation that longitudinal steadiness was affected to a much greater extent by changes in static margin than by changes in rotational damping. The best longitudinal steadiness was noted at large values of static margin. For all values of rotational damping, the steadiness of the model decreased as the static margin was reduced. The model was especially unsteady at low values of static margin (0.03 or less). Reduction in rotational damping had little effect on longitudinal steadiness, except that with low values of static margin (0.03 or less) the longitudinal divergences were sometimes more violent with the tailless (low rotational damping) condition.
Book Synopsis Effects of Landing Gear, Speed Brake and Protuberances on the Longitudinal Aerodynamic Characteristics of an NASA Supercritical-wing Research Airplane Model by :
Download or read book Effects of Landing Gear, Speed Brake and Protuberances on the Longitudinal Aerodynamic Characteristics of an NASA Supercritical-wing Research Airplane Model written by and published by . This book was released on 1975 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Longitudinal and Lateral Controls on Winged Reentry Configuration at Mach 1.97 and Angles of Attack Up to 90° by : Gerald V. Foster
Download or read book Effect of Longitudinal and Lateral Controls on Winged Reentry Configuration at Mach 1.97 and Angles of Attack Up to 90° written by Gerald V. Foster and published by . This book was released on 1961 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Induced Interference Effects on the Aerodynamic Characteristics of a 0.16-scale Six-jet V/STOL Model in Transition by : Matthew M. Winston
Download or read book Induced Interference Effects on the Aerodynamic Characteristics of a 0.16-scale Six-jet V/STOL Model in Transition written by Matthew M. Winston and published by . This book was released on 1970 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Evaluation of the Aerodynamic Interference of the Tunnel 4T Captive Trajectory System on the Separation Characteristics of the BLU-27 Store by : Wallace Luchuk
Download or read book Evaluation of the Aerodynamic Interference of the Tunnel 4T Captive Trajectory System on the Separation Characteristics of the BLU-27 Store written by Wallace Luchuk and published by . This book was released on 1976 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains the results of an experimental program to evaluate the effect of the 4T Captive Trajectory System on the separation characteristics of typical stores. The models selected as being generally representative of external stores were the modified BLU-27B/B configuration with and without fins. The aircraft model selected for this test was the F-111. To assess the aerodynamic interference of the Captive Trajectory System on the store and its trajectory, four sting lengths were used to position the store model at varying distances from the support system. Data were obtained at Mach numbers of 0.4, 0.8, 0.9, 1.1, and 1.2. Captive trajectories simulating store separation from the aircraft model were obtained; forces on the store were measured while the store was moved vertically away from the marriage position; and force data on the store were obtained as it was yawed in a location as far removed as possible from the aircraft model. It was concluded that the Captive Trajectory System has little or no effect on the store loads and trajectory development. (Author).
Book Synopsis Some Measurements of the Interference of a Sting Support on the Pressure Distribution on a Rear Fuselage and Tailplane at Subsonic Speeds by : E. C. Carter
Download or read book Some Measurements of the Interference of a Sting Support on the Pressure Distribution on a Rear Fuselage and Tailplane at Subsonic Speeds written by E. C. Carter and published by . This book was released on 1967 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Sting Interference Effects on the SDM Aircraft as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.3 Through 1.3 by : F. B. Cyran
Download or read book Sting Interference Effects on the SDM Aircraft as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.3 Through 1.3 written by F. B. Cyran and published by . This book was released on 1980 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the effects of sting-support interference on the measurement of pitch damping, yaw-damping, pitching-moment slope, yawing-moment slope, pitching moment, and base pressure. The model was the Standard Dynamics Model (SDM). The forced oscillation technique was used to obtain data at Mach numbers 0.3 to 1.3 and Reynolds numbers, based on the model mean aerodynamic chord (MAC), of 0.3 million to 3.1 million. Amplitudes of oscillation were 1.0, 1.5, and 2.0 deg, and the reduced frequency parameter ranged from 0.009 to 0.032 radians.
Book Synopsis Effect of Canard Location and Size on Canard-wing Interference and Aerodynamic-center Shift Related to Maneuvering Aircraft at Transonic Speeds by : Blair B. Gloss
Download or read book Effect of Canard Location and Size on Canard-wing Interference and Aerodynamic-center Shift Related to Maneuvering Aircraft at Transonic Speeds written by Blair B. Gloss and published by . This book was released on 1974 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Longitudinal, Directional, and Lateral Stability and Control Data at a Mach Number of 6.83 of the Final Configuration of the X-15 Research Airplane by : Jim A. Penland
Download or read book Static Longitudinal, Directional, and Lateral Stability and Control Data at a Mach Number of 6.83 of the Final Configuration of the X-15 Research Airplane written by Jim A. Penland and published by . This book was released on 1960 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
