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 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 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 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 Aerodynamic Load Characteristics of Six 0 05 Scale Stores in the Flow Field of an F 4C Aircraft at Mach Numbers from 0 5 to 1 1 written by G. R. Gomillion and published by . This book was released on 1976 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel tests were conducted using six 0.05-scale stores with various afterbody shapes to investigate the store aerodynamic load characteristics in the flow field of the F-4C aircraft. The store models had a hemispherical nose and a cylindrical midsection with various afterbody shapes. Three store models had cruciform pattern fins on a blunted cone-shaped afterbody. The other three store models had blunted cone, blunted ogive, and cylindrical-shaped afterbodies, respectively. All finned store models were tested in both 'X' and '+' fin orientations. Free-Stream store loads data were also obtained at yaw angles between -6 and 30 deg. All store loads data are presented for Mach numbers from 0.5 to 1.1. (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 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 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 Flight Stability and Automatic Control written by Robert C. Nelson and published by WCB/McGraw-Hill. This book was released on 1998 with total page 441 pages. Available in PDF, EPUB and Kindle. Book excerpt: The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.
Download or read book Flow field Properties Near an Arrow wing written by Robert L. Weirich and published by . This book was released on 1968 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Measured and Calculated Flow Conditions on the Forward Fuselage of the X 15 Airplane and Model at Mach Numbers from 3 0 to 8 0 written by Murray Palitz and published by . This book was released on 1966 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Wing and Tail Location on the Aerodynamic Characteristics of an Airplane for Mach Numbers from 0 25 To 4 63 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-13 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental investigations have been conducted to determine the effect of wing vertical position and horizontal-tail vertical and axial position on the static aerodynamic characteristics of a wing-body horizontal-tail configuration. The configurations investigated included the wing in a high, mid, or low position on the body with the horizontal tail in each of these vertical positions as well as in three axial positions. The closest position of the horizontal tail to the wing essentially provided on all-wing configuration. In addition, tests were made for the three wing positions with the horizontal tail removed. The tests were made in three different wind tunnels to provide data for a Mach number range from 0.25 to 4.63. The purpose of the investigation was to illustrate the strong effects of interference flow fields as a function of geometry and flight regime. An analysis of the results indicate some arrangements that might lead to aerodynamic problems and others in which the interference flow fields might be favorably exploited. The results suggest that a coplanar concept with a translating horizontal tail could potentially minimize the aerodynamic changes with Mach number and provide more optimum performance over the Mach number range. Spearman, M. L. Langley Research Center NASA-TM-84643, NAS 1.15:84643 RTOP 505-43-43-01...
Download or read book Flight Test Results from the Rake Airflow Gage Experiment on the F 15b Airplane written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Rake Airflow Gage Experiment involves a flow-field survey rake that was flown on the Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center using the Dryden F-15B research test bed airplane. The objective of this flight test was to ascertain the flow-field angularity, local Mach number profile, total pressure distortion, and dynamic pressure at the aerodynamic interface plane of the Channeled Centerbody Inlet Experiment. This new mixed-compression, supersonic inlet is planned for flight test in the near term. Knowledge of the flow-field characteristics at this location underneath the airplane is essential to flight test planning and computational modeling of the new inlet, an
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 0 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 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 Effect of Various External Stores on the Static Longitudinal Stability Longitudinal Control and Drag Characteristics of the Model F 4C Airplane written by J. M. Whoric and published by . This book was released on 1973 with total page 143 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results from analysis of data obtained from wind tunnel tests, which were conducted to determine the effect of various external stores on the aerodynamic characteristics of the model F-4C airplane, are presented and discussed. The analysis includes evaluation of the static longitudinal stability, drag, and longitudinal control characteristics of the F-4C when loaded with the Pavestorm missile series, Modular Weapons series, Mark 84 EOGB, M-118 LGB, SUU-51B/B, SUU-30H/B, and Rockeye stores. Moreover, analysis of the probable cause as well as the wind tunnel verification of a pilot-reported 'tuck-under' problem with the F-4C when carrying the Pavestorm series of stores is presented and discussed. Incremental drag rise and neutral point shift associated with store loading are compared with results obtained from existing prediction methods and techniques. Data are presented for aircraft weights representative of each store loading at altitudes of sea level, 10-, 20-, and 30-thousand feet for aircraft center-of-gravity locations of 25, 33, and 36 percent of the mean aerodynamic chord over the Mach number range from 0.4 to 1.3. (Author).
