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Static Longitudinal And Lateral Aerodynamic Characteristics At A Mach Number Of 220 Of A V Stol Airplane Configuration With A Variable Sweep Wing And With A Skewed Wing Design
Download Static Longitudinal And Lateral Aerodynamic Characteristics At A Mach Number Of 220 Of A V Stol Airplane Configuration With A Variable Sweep Wing And With A Skewed Wing Design full books in PDF, epub, and Kindle. Read online Static Longitudinal And Lateral Aerodynamic Characteristics At A Mach Number Of 220 Of A V Stol Airplane Configuration With A Variable Sweep Wing And With A Skewed Wing Design 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 Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.20 of a Variable-wing-sweep STOL Configuration by : Gerald V. Foster
Download or read book Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.20 of a Variable-wing-sweep STOL Configuration written by Gerald V. Foster and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.01 of a Tailless Delta V/STOL Configuration Having Variable-sweep Wing Panels by : M. Leroy Spearman
Download or read book Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.01 of a Tailless Delta V/STOL Configuration Having Variable-sweep Wing Panels written by M. Leroy Spearman and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government-wide Index to Federal Research & Development Reports by :
Download or read book Government-wide Index to Federal Research & Development Reports written by and published by . This book was released on 1966 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Longitudinal Aerodynamic Characteristics at Mach Numbers from 0.50 to 1.19 of a Supersonic Transport Model with a Modified M Wing by : Edward J. Ray
Download or read book Longitudinal Aerodynamic Characteristics at Mach Numbers from 0.50 to 1.19 of a Supersonic Transport Model with a Modified M Wing written by Edward J. Ray and published by . This book was released on 1967 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics in Pitch at a Mach Number of 1.97 of Two Variable-wing- Sweep V/STOL Configurations with Outboard Wing Panels Swept Back 75° by : Gerald V. Foster
Download or read book Aerodynamic Characteristics in Pitch at a Mach Number of 1.97 of Two Variable-wing- Sweep V/STOL Configurations with Outboard Wing Panels Swept Back 75° written by Gerald V. Foster and published by . This book was released on 1960 with total page 30 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 Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 by : Samuel M. Dollyhigh
Download or read book Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 written by Samuel M. Dollyhigh and published by . This book was released on 1971 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location.
Book Synopsis Supersonic Aerodynamic Characteristics of a Low-Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1.86 and a Body of Fineness Ratio 20 by :
Download or read book Supersonic Aerodynamic Characteristics of a Low-Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1.86 and a Body of Fineness Ratio 20 written by and published by . This book was released on 1960 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
Book Synopsis Aerodynamic characteristics at Mach 6 of a hypersonic research airplane concept having a 70 ̊swept delta wing by : Louis E. Clark
Download or read book Aerodynamic characteristics at Mach 6 of a hypersonic research airplane concept having a 70 ̊swept delta wing written by Louis E. Clark and published by . This book was released on 1977 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Longitudinal and Lateral-directional Aerodynamic Characteristics of a Wing-cone Configuration at Mach Numbers from 2.5 to 4.5 by : Peter F. Covell
Download or read book Longitudinal and Lateral-directional Aerodynamic Characteristics of a Wing-cone Configuration at Mach Numbers from 2.5 to 4.5 written by Peter F. Covell and published by . This book was released on 1992 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics at Transonic and Supersonic Speeds of a Rocket-propelled Airplane Configuration Having a Diamond-plan-form Wing Aspect Ration 3.08 and a Low, Swept Horizontal Tail by : Alan B. Kehlet
Download or read book Aerodynamic Characteristics at Transonic and Supersonic Speeds of a Rocket-propelled Airplane Configuration Having a Diamond-plan-form Wing Aspect Ration 3.08 and a Low, Swept Horizontal Tail written by Alan B. Kehlet and published by . This book was released on 1954 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of an F-8 Aircraft Configuration with a Variable Camber Wing at Mach Numbers from 1.5 to 2.0 by :
Download or read book Aerodynamic Characteristics of an F-8 Aircraft Configuration with a Variable Camber Wing at Mach Numbers from 1.5 to 2.0 written by and published by . This book was released on 1977 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 by : Howard F. Savage
Download or read book The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 written by Howard F. Savage and published by . This book was released on 1957 with total page 662 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.
Book Synopsis Longitudinal Aerodynamic Characteristics of a High-subsonic-speed Transport Airplane Model with a Cambered 40° Sweptback Wing of Aspect Ratio 8 at Mach Numbers to 0.96 by : Atwood R. Heath
Download or read book Longitudinal Aerodynamic Characteristics of a High-subsonic-speed Transport Airplane Model with a Cambered 40° Sweptback Wing of Aspect Ratio 8 at Mach Numbers to 0.96 written by Atwood R. Heath and published by . This book was released on 1960 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
