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Static Force Tests Of A Model Of A Twin Jet Fighter Airplane For Angles Of Attack From 100 To 1100 And Sideslip Angles From 400 To 400
Download Static Force Tests Of A Model Of A Twin Jet Fighter Airplane For Angles Of Attack From 100 To 1100 And Sideslip Angles From 400 To 400 full books in PDF, epub, and Kindle. Read online Static Force Tests Of A Model Of A Twin Jet Fighter Airplane For Angles Of Attack From 100 To 1100 And Sideslip Angles From 400 To 400 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Static Force Tests of a Model of a Twin-jet Fighter Airplane for Angles of Attack from -100 to 1100 and Sideslip Angles from -400 to 400 by : Ernie L. Anglin
Download or read book Static Force Tests of a Model of a Twin-jet Fighter Airplane for Angles of Attack from -100 to 1100 and Sideslip Angles from -400 to 400 written by Ernie L. Anglin and published by . This book was released on 1971 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static force tests of model of twin jet fighter aircraft at various angles of attack and sideslip angles to obtain data for theoretical spin studies.
Book Synopsis Dynamic Stability Derivatives of a Twin-jet Fighter Model for Angles of Attack from -10 ̊to 110 ̊ by : Sue B. Grafton
Download or read book Dynamic Stability Derivatives of a Twin-jet Fighter Model for Angles of Attack from -10 ̊to 110 ̊ written by Sue B. Grafton and published by . This book was released on 1971 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed investigation was conducted to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -10 [degree] to 110 [degree] for a twin-jet swept-wing fighter model. Several frequencies and amplitudes were investigated to determine the effects of these variables on the stability derivatives. The effect of the vertical and horizontal tail, and horizontal-tail incidence on the derivatives was also evaluated. The results indicate that the model exhibited stable values of damping in pitch over the entire angle-of-attack range, but marked reductions of damping in roll were measured at the stall, and unstable values of damping in yaw were present for the very high angles of attack associated with flat spins. Either removal of the horizontal or vertical tail or full up deflection of the horizontal tail eliminated the unstable characteristics of the damping-in-yaw derivatives.
Book Synopsis Captive Aircraft Testing at High Angles of Attack by : R. W. Butler
Download or read book Captive Aircraft Testing at High Angles of Attack written by R. W. Butler and published by . This book was released on 1981 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A captive testing technique capable of simulating aircraft maneuvers at high angles of attack has been developed and tested in the Aerodynamic Tunnel 16T of the Arnold Engineering Development Center (AEDC). The captive technique uses a closed loop system between wind tunnel, model, and computer. Use of the wind tunnel as an analog forcing function eliminates the requirement for a conventional static data matrix in motion simulation. Various high angle-of-attack maneuvers (rudder roll, aileron roll, wind-up turn, etc.) were generated with the captive system and show good correlation with flight data. (Author).
Book Synopsis Investigation of the Dynamic Lateral Stability and Control Characteristics of a Model of a Fighter Airplane Without a Horizontal Tail and Equipped with Either Single Or Twin Vertical Tails by : John W. Draper
Download or read book Investigation of the Dynamic Lateral Stability and Control Characteristics of a Model of a Fighter Airplane Without a Horizontal Tail and Equipped with Either Single Or Twin Vertical Tails written by John W. Draper and published by . This book was released on 1949 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Lateral-directional Stability Characteristics of a Twin-jet Fighter Airplane at High Angles of Attack by : Joseph R. Chambers
Download or read book Analysis of Lateral-directional Stability Characteristics of a Twin-jet Fighter Airplane at High Angles of Attack written by Joseph R. Chambers and published by . This book was released on 1969 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Jet fighter aircraft lateral directional stability at high angles of attack.
Book Synopsis Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail by : Paul T. Soderman
Download or read book Full-scale Wind-tunnel Tests of a Small Unpowered Jet Aircraft with a T-Tail written by Paul T. Soderman and published by . This book was released on 1971 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.
Book Synopsis Control-Surface Deflection Effects on the Innovative Control Effectors (ICE 101) Design by : Gregory A. Addington
Download or read book Control-Surface Deflection Effects on the Innovative Control Effectors (ICE 101) Design written by Gregory A. Addington and published by . This book was released on 2000 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: A static wind tunnel test of the Innovative Controls Effectors (ICE 101) conceptual aircraft configuration was conducted in the Air Force Research Laboratory's Vertical Wind Tunnel. This entry characterized the increments to the aerodynamic loading provided by the various control surfaces while using a more finely-resolved test matrix in angle of attack and sideslip than typically seen in wind tunnel testing. The purpose for obtaining these data was to determine the effect which control surface deflection had on critical state locations in preparation for the test of a second ICE model built with remotely- actuated control surfaces. (Critical states are discrete flight mechanical states where the aerodynamic response looses its analytic dependence on one or more state variables.) These data demonstrate that the aerodynamic increments are in many cases at minimum nonlinear functions of the surface deflection angle, and strongly suggest that some critical states do shift in angle of attack and/or sideslip with changing deflection angle.
Book Synopsis Longitudinal Static Stability and Inlet Drag Characteristics of the McDonnell Douglas F-15 Tactical Fighter Aircraft at Mach Numbers of 1.60 and 2.20 by : F. J. Keeney
Download or read book Longitudinal Static Stability and Inlet Drag Characteristics of the McDonnell Douglas F-15 Tactical Fighter Aircraft at Mach Numbers of 1.60 and 2.20 written by F. J. Keeney and published by . This book was released on 1971 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Comparison of Data Obtained by Two Flight Techniques for Determining the Sideslip Characteristics of a Fighter Airplane by : Harold I. Johnson
Download or read book A Comparison of Data Obtained by Two Flight Techniques for Determining the Sideslip Characteristics of a Fighter Airplane written by Harold I. Johnson and published by . This book was released on 1945 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: In order to determine the validity of sideslip data obtained in flight by the continuous-record method, sideslip data obtained from a fighter airplane in slowly increasing sideslips have been compared with sideslip data obtained from the same airplane in sideslips in which all the flight conditions were stabilized. The results of the comparison showed no essential difference in the sideslip characteristics obtained by the two flight techniques even though the continuous sideslips were purposely executed with a yawing velocity about double the usual rate of 1° per second in order to accentuate the effects of the small yawing and rolling velocities inherent in the method. Approximate theoretical calculations confirmed the experimental results but indicated that rates of yawing or rolling lower than 1° per second are desirable if the continuous-sideslip technique is employed in testing airplanes much larger than current fighters. The method of measuring sideslip characteristics under steady conditions is preferred to the method of measuring sideslip characteristics in slowly increasing sideslips when the airplane is directionally unstable, when is has a large pitching moment due to sideslip, or when a poor relationship exists among the rudder, aileron, and elevator control forces in sideslips.
Book Synopsis Wind Tunnel Investigation of the Aerodynamic Hysteresis Phenomenon on the F-4 Aircraft and Its Effects on Aircraft Motion by : J. F. Herman
Download or read book Wind Tunnel Investigation of the Aerodynamic Hysteresis Phenomenon on the F-4 Aircraft and Its Effects on Aircraft Motion written by J. F. Herman and published by . This book was released on 1980 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel test program and an analytical study were conducted to investigate aerodynamic hysteresis phenomena on the F-4 aircraft. The wind tunnel test was conducted in the Arnold Engineering Development Center (AEDC) Aerodynamic Wind Tunnel (4T) to investigate the source of aerodynamic hysteresis in static aerodynamic data. The wind tunnel test also provided data that were used in a motion simulation study of the effect of hysteresis on predicted aircraft motion. Static longitudinal lateral directional force and moment data and wing pressure data were obtained on a 0.5-scale model (without pylons or external stores) with various simulated leading-edge slats. These data include the effects of Mach number, angle of attack, model movement, and time dependence on the aerodynamic hysteresis characteristics. Data are presented for the Mach number range from 0.7 to 0.95 at angles of attack from -4 to 24 deg at zero deg sideslip angle and for sideslipe angles from -12 to 12 deg at angles of attack of 5, 10, 15, and 20 deg. Six-degrees-of-freedom motion simulation studies were used to assess the effect of hysteresis in the rolling-moment coefficient on the prediction of aircraft motion. Simulations of various flight maneuvers were conducted both with and without hysteresis in the aerodynamic data. (Author).
Book Synopsis 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 by : Edward C. Polhamus
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.
Book Synopsis Pressure and Static Force Test of Three Elliptic Missile Body Configurations at Mach Numbers 1.5 to 5.0 by : M. E. Sellers
Download or read book Pressure and Static Force Test of Three Elliptic Missile Body Configurations at Mach Numbers 1.5 to 5.0 written by M. E. Sellers and published by . This book was released on 1983 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Large Angle Motion Tests, Including Spins, of a Free-Flying Radio-Controlled 0.13-Scale Model of a Twin-Jet Swept-Wing Fighter Airplane by :
Download or read book Large Angle Motion Tests, Including Spins, of a Free-Flying Radio-Controlled 0.13-Scale Model of a Twin-Jet Swept-Wing Fighter Airplane written by and published by . This book was released on 1961 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length by : Carlton S. James
Download or read book Aerodynamic Performance and Static Stability at Mach Number 3.3 of an Aircraft Configuration Employing Three Triangular Wing Panels and a Body Equal Length written by Carlton S. James and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An aircraft configuration, previously conceived as a means to achieve favorable aerodynamic stability characteristics., high lift-drag ratio, and low heating rates at high supersonic speeds., was modified in an attempt to increase further the lift-drag ratio without adversely affecting the other desirable characteristics. The original configuration consisted of three identical triangular wing panels symmetrically disposed about an ogive-cylinder body equal in length to the root chord of the panels. This configuration was modified by altering the angular disposition of the wing panels, by reducing the area of the panel forming the vertical fin, and by reshaping the body to produce interference lift. Six-component force and moment tests of the modified configuration at combined angles of attack and sideslip were made at a Mach number of 3.3 and a Reynolds number of 5.46 million. A maximum lift-drag ratio of 6.65 (excluding base drag) was measured at a lift coefficient of 0.100 and an angle of attack of 3.60. The lift-drag ratio remained greater than 3 up to lift coefficient of 0.35. Performance estimates, which predicted a maximum lift-drag ratio for the modified configuration 27 percent greater than that of the original configuration, agreed well with experiment. The modified configuration exhibited favorable static stability characteristics within the test range. Longitudinal and directional centers of pressure were slightly aft of the respective centroids of projected plan-form and side area.
Book Synopsis Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under the Wing of a Tactical Fighter Aircraft at Supersonic Speeds by : J. C. Donaldson
Download or read book Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under the Wing of a Tactical Fighter Aircraft at Supersonic Speeds written by J. C. Donaldson and published by . This book was released on 1973 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Book Synopsis Static Force Tests at Mach 8 of Sharp and Blunt 20-deg Half-angle Cones with a Blunt 70-deg Swept Delta Wing by : G. H. Merz
Download or read book Static Force Tests at Mach 8 of Sharp and Blunt 20-deg Half-angle Cones with a Blunt 70-deg Swept Delta Wing written by G. H. Merz and published by . This book was released on 1962 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Variation of Maximum Lift for a Pitching Airplane Model and Comparison with Flight Results by : Paul W. Harper
Download or read book Investigation of the Variation of Maximum Lift for a Pitching Airplane Model and Comparison with Flight Results written by Paul W. Harper and published by . This book was released on 1948 with total page 706 pages. Available in PDF, EPUB and Kindle. Book excerpt: Apparatus was developed which utilized a pitching airplane model to determine maximum wing loads as a function of the rate of change of angle of attack. In order to evaluate the pitching-model technique, the maximum lift coefficient was determined as a function of the rate of change of angle of attack over a Mach number range from approximately 0.2 to 0.6 in wind-tunnel tests of a 1/20-scale model of a conventional single-engine fighter airplane and was conpared with existing flight data of this airplane. The wind-tunnel and flight results were found to be in good agreement.
