Download or read book An Investigation of the Effects of Nose Geometry on the Aerodynamic Characteristics of a Full Scale Vertical Launch ASROC Forebody at M00 written by R. M. Vaeth and published by . This book was released on 1987 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Fuselage Forebody Geometry on Low speed Lateral directional Characteristics of Twin tail Fighter Model at High Angles of Attack written by Peter C. Carr and published by . This book was released on 1979 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Nose Bluntness and Afterbody Shape on Aerodynamic Characteristics of a Monoplanar Missile Concept with Bodies of Circular and Elliptical Cross Sections at a Mach Number of 2 50 written by Ernald B. Graves and published by . This book was released on 1979 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of a Pointed Nose on Spin Characteristics of a Fighter Airplane Model Including Correlation with Theoretical Calculations written by Joseph R. Chambers and published by . This book was released on 1970 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of the Aerodynamic Characteristics of Two Preliminary Designs of Scout Research Vehicle at Mach Numbers from 1 77 to 4 65 written by Robert J. Keynton and published by . This book was released on 1961 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Forebody Strakes on the Aerodynamic Characteristics in Pitch and Sideslip of a Hypersonic Airplane Configuration at Mach Numbers of 1 41 2 01 and 6 86 written by Cornelius Driver and published by . This book was released on 1959 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Influence of Forebody Geometry on Aerodynamic Characteristics and a Design Guide for Defining Departure spin Resistant Forebody Configurations written by William Bihrle (Jr) and published by . This book was released on 1989 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt: The loss of airplanes and occupants attributable to departures from controlled flight and ensuing spins has been a problem since the earliest days of aviation. These losses have plagued both the military and general aviation communities. The phenomena responsible for such losses take on added significance because, in the past ten years, high angle-of-attack capability in the post-stall region has been shown to significantly enhance the air combat maneuvering effectiveness of fighter airplanes and, therefore, this is not a region to be avoided, but rather exploited, if possible. Fortunately, the aerodynamic characteristics that produce departures and spins have been identified within the past few years through rotary balance tests, which identify an airplane's aerodynamic characteristics in a steady rotational flow environment. It was demonstrated in the Phase I that the high angle-of-attack aerodynamic characteristics are very configuration dependent and that forebody geometry can have a significant influence on these characteristics. In the extreme case, an aircraft's undesirable aerodynamics can be completely attributable to the forebody. In this instance, autorotative yawing and rolling moments, as well as increasing nose-up pitching moments with increasing rotation rate, are realized.

Download or read book Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 55 Deg Cropped Delta Wing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 174 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel data base was established for the effects of chine-like forebody strakes and Mach number on the longitudinal and lateral-directional characteristics of a generalized 55 degree cropped delta wing-fuselage-centerline vertical tail configuration. The testing was conducted in the 7- by 10-Foot Transonic Tunnel at the David Taylor Research Center at free-stream Mach numbers of 0.40 to 1.10 and Reynolds numbers based on the wing mean aerodynamic chord of 1.60 x 10(exp 6) to 2.59 x 10(exp 6). The best matrix included angles of attack from 0 degree to a maximum of 28 degree, angles of sidesip of 0, +5, and -5 degrees, and wing leading-edge flat deflection angles of 0 and 30 degrees. Key flow phenomena at subsonic and transonic conditions were identified by measuring off-body flow visualization with a laser screen technique. These phenomena included coexisting and interacting vortex flows and shock waves, vortex breakdown, vortex flow interactions with the vertical tail, and vortices induced by flow separation from the hinge line of the deflected wing flap. The flow mechanisms were correlated with the longitudinal and lateral-directional aerodynamic data trends. Erickson, Gary E. and Rogers, Lawrence W. Langley Research Center AERODYNAMIC CHARACTERISTICS; DELTA WINGS; FLOW CHARACTERISTICS; FOREBODIES; LATERAL STABILITY; LONGITUDINAL STABILITY; MACH NUMBER; STRAKES; WIND TUNNEL TESTS; AIRFOIL PROFILES; ANGLE OF ATTACK; BOUNDARY LAYER SEPARATION; CHORDS (GEOMETRY); FLOW VISUALIZATION; SHOCK WAVES; VORTEX BREAKDOWN; VORTICES; WING FLAPS...

Download or read book Effects of Body and Fin Deflections on the Aerodynamic Characteristics in Pitch of a 0 065 scale Model of a Four stage Rocket Configuration at Mach Numbers of 1 41 and 1 82 written by Ross B. Robinson and published by . This book was released on 1959 with total page 38 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 Wind tunnel Investigation of the Aerodynamic and Structural Deflection Characteristics of the Goodyear Inflatoplane written by Bennie W. Cocke (Jr.) and published by . This book was released on 1958 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation has been conducted in the Langley full-scale tunnel to determine the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane over a range of test velocities from minimum stall speed up to speeds giving load factors for wing buckling. Tests were conducted over a range of speeds from approximately 41 to 70 mph with wing-guy-cable loads, wing-distortion photographs, and aerodynamic-force data recorded at each speed for a full range of angle of attack.

Download or read book Effect of First stage Geometry on Aerodynamic Characteristics in Pitch of Two stage Rocket Vehicles from Mach 1 57 to 2 86 written by William A. Corlett and published by . This book was released on 1965 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Static and Rotational Aerodynamic Data from O to 90 Angle of Attack for a Series of Basic and Altered Forebody Shapes written by William Bihrle (Jr) and published by . This book was released on 1989 with total page 372 pages. Available in PDF, EPUB and Kindle. Book excerpt: The loss of airplanes and occupants attributable to departures from controlled flight and ensuing spins has been a problem since the earliest days of aviation. These losses have plagued both the military and general aviation communities. The phenomena responsible for such losses take on added significance because, in the past ten years, high angle-of-attack capability in the post-stall region has been shown to significantly enhance the air combat maneuvering effectiveness of fighter airplanes and, therefore, this is not a region to be avoided, but rather exploited, if possible. Fortunately, the aerodynamic characteristics that produce departures and spins have been identified within the past few years through rotary balance tests, which identify an airplane's aerodynamic characteristics in a steady rotational flow environment. It was demonstrated in the Phase I that the high angle-of-attack aerodynamic characteristics are very configuration dependent and that forebody geometry can have a significant influence on these characteristics. In the extreme case, an aircraft's undesirable aerodynamics can be completely attributable to the forebody. In this instance, autorotative yawing and rolling moments, as well as increasing nose-up pitching moments with increasing rotation rate, are realized.

Download or read book Low Speed High Lift Aerodynamic Characteristics of Slender Hypersonic Accelerator Type Configurations written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-05 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two investigations were conducted in the Langley 14 by 22 Foot Subsonic Tunnel to determine the low-speed aerodynamic characteristics of a generic hypersonic accelerator-type configuration. The model was a delta wing configuration incorporating a conical forebody, a simulated wrap-around engine package, and a truncated conical aftbody. Six-component force and moment data were obtained over a range of attack from -4 to 30 degrees and for a sideslip range of + or - 20 degrees. In addition to tests of the basic configuration, component build-up tests were conducted; and the effects of power, forebody nose geometry, canard surfaces, fuselage strakes, and engines on the lower surface alone were also determined. Control power available from deflections of wing flaps and aftbody flaps was also investigated and found to be significantly increased during power-on conditions. Large yawing moments resulted from asymmetric flow fields exhibited by the forebody as revealed by both surface pressure data and flow visualization. Increasing nose bluntness reduced the yawing-moment asymmetry, and the addition of a canard eliminated the yawing-moment asymmetry. Gatlin, Gregory M. Langley Research Center RTOP 763-01-31-22...

Download or read book Numerical Investigation of Aerodynamics of Canard controlled Missile Using Planar and Grid Tail Fins written by James DeSpirito and published by . This book was released on 2004 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flow field around a canard-controlled missile in subsonic and transonic flow. Computations were performed at Mach 0.6 and 0.9, six angles of attack between 0 deg and 10 deg, and with planar and grid tail fins. The computations were validated with wind tunnel data. Flow visualizations showed that the canard downwash produced a low-pressure region on the starboard side of the missile that produced a large induced side force. The canard trailing vortices interacted with the tail fins until alpha> 8 deg, producing a pressure differential on the leeward tail fin, leading to the adverse induced roll effects. Visualizations of the flow through the grid fin structure showed choking of the flow at Mach 0.9 and Mach 1.5. The validated simulations results showed that grid fins did not improve the canard roll-control effectiveness at subsonic and transonic speeds as well as they did at the low supersonic speed.

Download or read book Supersonic Aerodynamic Characteristics of an Advanced F 16 Derivative Aircraft Configuration written by Mike C. Fox and published by . This book was released on 1993 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Afterbody Geometry on Aerodynamic Characteristics of Isolated Nonaxisymmetric Afterbodies at Transonic Mach Numbers written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-24 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt: A parametric study was conducted in the Langley 16-Foot Transonic Tunnel on an isolated nonaxisymmetic fuselage model that simulates a twin-engine fighter. The effects of aft-end closure distribution (top/bottom) nozzle-flap boattail angle versus nozzle-sidewall boattail angle) and afterbody and nozzle corner treatment (sharp or radius) were investigated. Four different closure distributions with three different corner radii were tested. Tests were conducted over a range of Mach numbers from 0.40 to 1.25 and over a range of angles of attack from -3 to 9 degrees. Solid plume simulators were used to simulate the jet exhaust. For a given closure distribution in the range of Mach numbers tested, the sharp-corner nozzles generally had the highest drag, and the 2-in. corner-radius nozzles generally had the lowest drag. The effect of closure distribution on afterbody drag was highly dependent on configuration and flight condition. Bangert, Linda S. and Carson, George T., Jr. Langley Research Center NASA-TP-3236, L-17034, NAS 1.60:3236 RTOP 505-62-30-01...