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Sting Support Interference On Longitudinal Aerodynamic Characteristics Of Cargo Type Airplane Models At Mach 070 To 084
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Book Synopsis Sting-support Interference on Longitudinal Aerodynamic Characteristics of Cargo-type Airplane Models at Mach 0.70 to 0.84 by : Donald L. Loving
Download or read book Sting-support Interference on Longitudinal Aerodynamic Characteristics of Cargo-type Airplane Models at Mach 0.70 to 0.84 written by Donald L. Loving and published by . This book was released on 1967 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Aeronautical Journal written by and published by . This book was released on 1990 with total page 892 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 Effect of Wing Modifications on the Longitudinal Stability of a Tailless All-wing Airplane Model by : Charles L. Seacord
Download or read book Effect of Wing Modifications on the Longitudinal Stability of a Tailless All-wing Airplane Model written by Charles L. Seacord and published by . This book was released on 1945 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation of the power-off longitudinal stability characteristics of a tailless all-wing airplane model with various wing modifications has been made in the Langley free-flight tunnel. Force and tuft tests were made on the model in the original condition, with the wing tips rotated for washout, with rectangular and swept-forward tips, and with various slat arrangements. Flight tests were made with the original wing and with the original wing equipped with the most promising modifications. The results indicated that changes in tip plan form or rotation of the wing tips did not appreciably reduce the instability at high lift coefficients. Addition of wing slats, however, improved the longitudinal stability at the stall when the slat extended far enough inboard to cover the area that tended to stall first.
Book Synopsis An Investigation of F-16 Nozzle-afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference by : Earl A. Price (Jr.)
Download or read book An Investigation of F-16 Nozzle-afterbody Forces at Transonic Mach Numbers with Emphasis on Support System Interference written by Earl A. Price (Jr.) and published by . This book was released on 1979 with total page 416 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive experimental program was conducted to provide nozzle-afterbody data with a minimum interference support system on a 1/9-scale F-16 model and to determine the interference induced on the afterbody-nozzle region by a sting, a wingtip, and a strut model support system. The investigation was conducted over the Mach number range from 0.6 to 1.5 and at angles of attack from 0 to 9 deg. Interference was evaluated by comparison of nozzle-afterboy axial and normal forces obtained from integrating pressure data. The results include parametric studies of the efects of various components of the wingtip support system (i.e., the support blade axial position, wingtip boom diameter, boom spacing, and boom-tip axial location). High-pressure air at ambient temperature was utilized for exhaust plume simulation. The results indicate that a sting support passing through the nozzle with the jet effects simulated by an annular jet appears to offer a minimum interference support system for the type of nozzle-afterbody test described in this report.
Book Synopsis An Investigation of Sting Interference Effects on an Oscillating Cone in Transonic Flow by : Frederick B. Cyran
Download or read book An Investigation of Sting Interference Effects on an Oscillating Cone in Transonic Flow written by Frederick B. Cyran and published by . This book was released on 1981 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel sting support interference effects on dynamic stability derivatives, static pitching moment and base pressure of a blunt, 7-deg cone were investigated at subsonic and transonic Mach numbers. The cone was tested with sting configurations having a variable effective sting length ranging from 1 to 3.3 model base diameters, at angles of attack ranging from 0 to 30 deg. A forced-oscillation system was utilized to obtain data at a frequency of oscillation of approximately 5.3 Hz, and at an amplitude of 1 deg. The Reynolds number, based on model base diameter, was nominally 1.8 million, which produced a turbulent boundary layer over the aft portion of the model. The nature of the causes of these interference effects is discussed and analyzed with respect to sting length, type of measurement, and Mach number, with emphasis on defining critical sting length and on predicting minimal interference sting configurations for dynamic stability testing. The results showed that the critical sting length depended on the type of measurement used as the interference indicator, Mach number, and angle of attack. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting diameter-to-model base diameter (0.22) investigated. (Author).
Book Synopsis Interference on a Model Afterbody from Downstream Support Hardware at Transonic Mach Numbers by : Earl A. Price (Jr.)
Download or read book Interference on a Model Afterbody from Downstream Support Hardware at Transonic Mach Numbers written by Earl A. Price (Jr.) and published by . This book was released on 1981 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to parametrically study the interference on an afterbody model that would be produced by the aft-support blade used with a wingtip support system. Geometric variables included the blade axial location, thickness, span, chord, and leading- and trailing-edge contours. Data were obtained over the Mach number range from 0.6 to 1.2 with the model at zero angle of attack. Interference was evaluated by comparing afterbody drag from a reference configuration, which had the aft-support blade removed, to the various configurations with a blade installed. A reasonable correlation of the blade interference effects on the afterbody drag coefficient was obtained, which included the influence of support blade axial position and blockage. Decreasing blade leading-edge bluntness by a factor of two resulted in a significant reduction of interference in the Mach number range from 0.9 to 1.1. Significantly greater interference was measured without jet flow than with jet flow. It is shown that a Euler equation computer code is a useful tool for the design of minimum interference support systems. (Author).
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 Influences of Sting Support on Aerodynamic Loads Acting on Captive Store Models by : R. E. Dix
Download or read book Influences of Sting Support on Aerodynamic Loads Acting on Captive Store Models written by R. E. Dix and published by . This book was released on 1976 with total page 332 pages. Available in PDF, EPUB and Kindle. Book excerpt: In a series of wind tunnel tests, measurements were made of the aerodynamic loads acting on eight different store configurations mounted in the external captive position on a one-twentieth-scale model of the F-4C aircraft. Store models included blunt and contoured afterbody shapes, stable and unstable designs, and large (one per pylon) and small (rack-mounted) configurations. The tests were conducted in an effort to evaluate sting effects on captive store loads. Sting effects were considered to consist of two contributions: the effect of altering the afterbody of a store to allow insertion of a sting, and the effect of the presence of the sting. Altering the afterbody of an unstable store influenced captive loads less than altering a stable configuration. It was also determined that the presence of a sting affected most the pitching and yawing moments.
Book Synopsis NACA Research Memorandum by : George Lee
Download or read book NACA Research Memorandum written by George Lee and published by . This book was released on 1957 with total page 36 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.
Book Synopsis Analysis of Wind-tunnel Tests to a Mach Number of 0.90 of a Four-engine Propeller-driving Airplane Configuration Having a Wing with 40 Degrees Sweepback and an Aspect Ratio of 10 by : George G. Edwards
Download or read book Analysis of Wind-tunnel Tests to a Mach Number of 0.90 of a Four-engine Propeller-driving Airplane Configuration Having a Wing with 40 Degrees Sweepback and an Aspect Ratio of 10 written by George G. Edwards and published by . This book was released on 1956 with total page 658 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted at speeds up to a Mach number of 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration having a 40 degrees swept wing with an aspect ratio of 10. Results of wind-tunnel tests of a model representing such an airplane configuration (see NACA TN 3789) show that these effects are of most concern in the low-speed high-thrust flight regime. In the present report the low-speed data are analyzed to determine the source of the various effects and to indicate how the adverse effects can be reduced, and the high-speed data are discussed primarily from the standpoint of Mach number effects. The analysis of the low-speed data indicates that the large variations of longitudinal stabil.itywith angle of attack resulted primarily from passage of the tail into and out of the slipstream. The slipstream also created large lift increments on the wing, particularly with flaps deflected, which resulted in increases in stability (with increasing thrust coefficient) from the outboard propeller and decreases in stability from the inboard propeller. It was concluded that the longitudinal stabiltty characteristics of the model couldbe improved by moving the nacelles outward, increasing the tail height, and reducing the tail span.
Book Synopsis Effect of Fabric Deflection at High Speeds on the Aerodynamic Characteristics of the Horizontal Tail Surface of an SB2D-1 Airplane by : Carl F. Schueller
Download or read book Effect of Fabric Deflection at High Speeds on the Aerodynamic Characteristics of the Horizontal Tail Surface of an SB2D-1 Airplane written by Carl F. Schueller and published by . This book was released on 1945 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Results are presented of an investigation of a full-scale horizontal tail surface to determine the elevator-fabric deflection at high speeds and the aerodynamic effects of the fabric deflection. Two fabric-covered elevators, differing only in rib spacing, and a solid wooden elevator were tested. The first elevator had a rib spacing of approximately 4 inches. The second elevator had a rib spacing of approximately 8 inches, which is more nearly typical of the spacing currently used. Tests were carried to a maximum Mach number of 0.68 except for model configurations for which the maximum allowable loads were reached at lower speeds.
Book Synopsis Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.20 of a Model of an 82 Deg Delta Wing Airplane Having Auxiliary Variable-sweep Wing Panels by :
Download or read book Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.20 of a Model of an 82 Deg Delta Wing Airplane Having Auxiliary Variable-sweep Wing Panels written by and published by . This book was released on 1963 with total page 44 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 Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches by : Charles F. Whitcomb
Download or read book Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches written by Charles F. Whitcomb and published by . This book was released on 1956 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
