Download or read book Investigation of the Flow Field Beneath the Wing of the F 4C Aircraft with Various External Stores at Mach Number 0 85 written by David W Hill (Jr) and published by . This book was released on 1972 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted to measure the velocity vector components in the flow field beneath the wing of the F-4C aircraft at Mach number 0.85. A conical-tip pressure probe was used to measure the velocity vectors beneath the wing with configuration combinations of pylons, Triple Ejection Rack (TER), Multiple Ejection Rack (MER), M-117, MK-81, and MK-84 stores. Results of the test indicate that the severity of the upwash and sidewash flow increased with the addition of pylons, TER, MER, and stores. The M-117 stores on the TER and MER produced the most severe flow field distortions. Also, the longitudinal gradients o upwash and sidewash flow decreased with an increase in aircraft angle of attack.
Download or read book Flow Field Characteristics Beneath the F 4C Aircraft at Mach Numbers 0 50 and 0 85 written by Ronald E. Davis and published by . This book was released on 1970 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted to investigate the flow field characteristics beneath the F-4C aircraft at high subsonic speeds. A conical-tip probe was used to measure the velocity-vector components in the region near the aircraft at Mach numbers 0.50 and 0.85. Aerodynamic force and moment data were obtained on a model of the M-117 bomb both near the aircraft and in the free stream to further evaluate the flow field. Data were obtained with a clean-wing aircraft configuration and with several combinations of M-117 bombs on the inboard wing-pylon station plus a fuel tank on the outboard wing-pylon station. (Author).
Download or read book Flow Field Characteristics Beneath the F 4C Aircraft at Mach Numbers 0 50 and 0 85 written by and published by . This book was released on 1970 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted to investigate the flow field characteristics beneath the F-4C aircraft at high subsonic speeds. A conical-tip probe was used to measure the velocity-vector components in the region near the aircraft at Mach numbers 0.50 and 0.85. Aerodynamic force and moment data were obtained on a model of the M-117 bomb both near the aircraft and in the free stream to further evaluate the flow field. Data were obtained with a clean-wing aircraft configuration and with several combinations of M-117 bombs on the inboard wing-pylon station plus a fuel tank on the outboard wing-pylon station. (Author).
Download or read book A Wind Tunnel Test to Study the Mutual Interference of Multiple Bodies in the Flow Field of the F 4C Aircraft in the Transonic Speed Range written by A. A. Hesketh and published by . This book was released on 1979 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flow field Characteristics and Aerodynamic Loads on External Stores Near the Fuselage and Wing pylon Positions of a Swept wing fuselage Model at Mach Numbers of 0 4 and 0 7 written by R. H. Roberts and published by . This book was released on 1974 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental data were obtained to aid in the prediction of aerodynamic loads and separation-trajectory characteristics on stores under the influence of an aircraft flow field. Four types of data were obtained in the vicinity of a generalized aircraft model: (1) flow field surveys, using a 40-deg cone probe, to determine the local velocity field, (2) force and moment data on four store models, (3) pressure distribution data on an ogive-cylinder model, and (4) captive-trajectory store separation data on one store model. The generalized aircraft model consisted of a swept-wing/fuselage combination with rectangular, flow-through engine ducts.
Download or read book Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores Volume I Summary Report Tunnel Empty and Mach Number Survey Data Force and Moment Data and Pressure Data written by Stanley C Perkins (Jr) and published by . This book was released on 1977 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Flow velocities and static pressures were also measured near the tunnel walls to provide outer flow field information. This report presents the data obtained during the test program conducted in the 4T and 16T Wind Tunnels at Arnold Engineering Development Center. The Flow-field data were obtained at Mach numbers 0.925, 0.975, and 1.025 and constitute the major part of the data. Volume I is a summary report which gives detailed information on the test program and presents uncertainties associated with the various types of data taken in the 4T Wind Tunnel. The volume also presents tunnel-empty and Mach-number surveys, as well as tabulated force and moment and pressure data for the Mach number range 0.80 to 1.15 and angles of attack -2, -5, 0, 2, and 5.
Download or read book Technique Development for Predicting External Store Aerodynamic Effects on Aircraft Performance written by R. Dale Gallagher and published by . This book was released on 1972 with total page 470 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores Volume IV Mach Number 1 025 Flow Field Survey Data for the 4 Percent Thick Wing Body Combination written by Stanley C Perkins (Jr) and published by . This book was released on 1977 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume IV presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 1.025.
Download or read book Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores Volume II Mach Number 0 925 Flow Field Survey Data for the 4 Percent Thick Wing Body Combination written by Stanley C Perkins (Jr) and published by . This book was released on 1977 with total page 249 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume II, presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 0.925.
Download or read book Data Report for a Test Program to Study Transonic Flow Fields about Aircraft with Application to External Stores Volume III Mach Number 0 975 Flow Field Survey Data for the 4 Percent Thick Wing Body Combination written by Stanley C Perkins (Jr) and published by . This book was released on 1977 with total page 249 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test program was conducted to obtain measurements of flow velocities and static pressures in the vicinity of wing-body-store model (representative of a fighter-type aircraft) as well as surface pressures, forces, and moments on the model. Volume III presents the tabulated flowfield data for the 4-percent thick wing model at Mach number 0.975.
Download or read book Validation and Expansion of the Flow Angularity Technique for Predicting Store Separation Trajectories written by Stephen C. Korn and published by . This book was released on 1972 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the external flow fields caused by various weapon configurations on the wing of an F-4 aircraft, verifies assumptions made in the flow angularity technique, and presents the documentation for the 'Flow Angularity Computer Program' with example trajectories. The flow angularity program is presently capable of calculating the trajectories of stores off the inboard and outboard wing stations in either single, triple ejector rack, or multiple ejector rack configurations. The assumptions made in the flow angularity technique have been analyzed and generally validated as good approximations. (Author).
Download or read book Mutual Interference of Multiple Bodies in the Flow Field of the F 4C Aircraft in the Transonic Speed Range written by A. A. Hesketh and published by . This book was released on 1979 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel field was conducted to study the mutual interference of multiple bodies in the flow field of the F-4C aircraft. The test utilized 1/20-scale models of the F-4C aircraft, the MK-83 bomb (with and without fins) and the triple ejector rack (TER) to obtain aerodynamic loads on the MK-83 at, and near, the carriage position on the wing inboard pylon. Flow field data in the vicinity of the TER were also obtained. Test variables included aircraft angle of attack from -3 to 17 deg, freestream Mach number from 0.60 to 0.95, and aircraft configuration. Freestream aerodynamic loads data were also obtained on the MK-83 bomb model. (Author).
Download or read book Flow Field Characteristics Near the Midwing Weapons Pylon of the F 16 Aircraft at Mach Numbers from 0 4 to 0 95 written by E. G Allee (Jr) and published by . This book was released on 1976 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests using 0.0667-scale models were conducted to determine the characteristics of the flow field near the midwing weapons pylon (wing stations 3 and 7) of the f-16 aircraft. The investigation was conducted by positioning an MK-84 LDGP store at various locations beneath the pylon, by use of a pressure probe to measure the flow-field velocities and angles relative to the freestream, and by separation trajectories using the MK-84 LDGP launched from the pylon. Test conditions ranged from Mach number 0.4 to 0.95 for aircraft angles of attack from 0 to 16 deg. Wing leading-edge flaps of the F-16 model were set at angles of 0, 4, and 15 deg. All trajectories were obtained at a simulated altitude of 5,000 ft. (Author).
Download or read book Measured and Theoretical Flow Fields Behind a Rectangular and a Triangular Wing Up to High Angles of Attack at a Mach Number of 2 46 written by Frank J. Centolanzi and published by . This book was released on 1959 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Introduction to Aircraft Flight Mechanics written by Thomas R. Yechout and published by AIAA. This book was released on 2003 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
Download or read book An Experimental Investigation at a Mach Number of 4 95 of Flow in the Vicinity of a 90 Degree Interior Corner Alined with the Free stream Velocity written by P. Calvin Stainback and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The AFFDL Nielsen Flow field Study written by William T Strike (Jr.) and published by . This book was released on 1976 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: This test was conducted in support of a program to develop a generalized analytical method for predicting the separation characteristics of stores from a high-speed aircraft (parent body). The tests were conducted in the von Karman Gas Dynamics Facility (VKF), Tunnel A, at nominal Mach numbers of 1.5, 1.76, 2.0, and 2.5 at a nominal free-stream Reynolds number of 4 x 10 to 6th power per foot. The test program involved three phases, namely flow-field surveys using a cone probe rake to determine local flow-field angles and velocity, pressure distributions on the store as it separated from a parent body, and six-component force and moment data on the store. The tests were conducted at angles of attack of zero and five degrees. This document contains a detailed description of the calibration procedure for the 20-deg half-angle cone probes and the method used to evaluate the local flow-field properties from the cone probe surface pressure and pitot pressure measurements. Also included is a comparison of integrated pressure data with the force and moment data obtained on the storebody by a balance. (Author).
