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 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 25 and 0 70 written by Willard E. Summers and published by . This book was released on 1970 with total page 0 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 0 40 and 0 70 written by Robert H. Roberts and published by . This book was released on 1971 with total page 86 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 Phase V written by and published by . This book was released on 1974 with total page 0 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 Aerodynamics Interference written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel and published by . This book was released on 1971 with total page 512 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).
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 AGARD Conference Proceedings written by North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development and published by . This book was released on 1971 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Loads and Separation Trajectories for Several Stores with the F 15 Aircraft at Mach Numbers from 0 6 to 1 3 written by and published by . This book was released on 1977 with total page 73 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel test was conducted at Mach numbers from 0.6 to 1.3 with 0.05-scale models of six stores and the F-15 aircraft. Extensive aerodynamic loads measurements were obtained for these stores in the aircraft flow field from the carriage position to 20 ft below the inboard pylon surfaces, with the majority of the data taken near the right-wing pylon. Aircraft angle of attack was varied from 0 to 10 deg. Separation trajectories were obtained for three of the stores at simulated altitudes from 5,000 to 18,000 ft at an aircraft angle of 0.5 deg. Free-stream characteristics for all stores were obtained with the aircraft model removed from the tunnel.
Download or read book Effects of External Stores on the Static Longitudinal Aerodynamic Characteristics of a Model of a 45 Degree Swept wing Fighter Airplane at Mach Numbers of 1 61 and 2 01 written by Gerald V. Foster and published by . This book was released on 1956 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of various external-store configurations of the longitudinal and lateral aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane. Pylon-mounted stores located at 23.8, 46.2, and 67.0 percent of the wing semispan were tested individually and in various combinations. The inboard stores relative to outboard stores were similar in shape but approximately 25 percent greater in size. The stores located at 46.2 percent of the wing semispan represented a large fuel tank and had an unsymmetrical shape.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Comparison of Measured and Predicted Indicated Angles of Attack Near the Fuselages of a Triangular wing Wind tunnel Model and a Swept wing Fighter Airplane in Flight written by Norman M. McFadden and published by . This book was released on 1953 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Comparisons are presented of predicted values of flow angles and those measured using detectors close to the surface of the forward portion of fuselages of a large-scale, triangular-wing, wind-tunnel model at low speeds and a 35° swept-wing fighter airplane in flight. Effects of flap deflection on the upwash of the triangular-wing model are included.
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 Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical tail load Characteristics of a Complete Model Having a Delta Wing written by Edward C. Polhamus and published by . This book was released on 1958 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.
Download or read book Flutter Characteristics of Swept Wings at Transonic Speeds written by Laurence K. Loftin and published by . This book was released on 1955 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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).
