Download or read book Wind Tunnel Investigation of the Forces and Moments Acting on a Cruciform Finned Model with Fixed and Freely Spinning Tail Assemblies at a Mach Number of 2 0 written by William E. DeGrafft and published by . This book was released on 1963 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Spinning cruciform finned models were tested to determine the normal force, pitching moment, side force and yawing moment characteristics at a Mach number of 2.0 and a free stream Reynolds number of 3.98 x 10 to the 6th power per foot. The models had fin cant angles of 0, 2 and 4 degrees. In addition the models with the 2 and 4 degree fin cant angles were constructed so that the fin assembly could rotate either with the body as a single unit or rotate freely with the body locked. The tests showed that for the spin rates developed during the test, the normal force and pitching moments for all models are independ ent of spin rate and fin cant angle. The yawing moment is reduced on the average by a factor of 0.76 if the fins are allowed to rotate freely while the body is held stationary. (Author).

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1963 with total page 1342 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Abstract Bulletin written by Defense Documentation Center (U.S.) and published by . This book was released on 1964 with total page 1148 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book U S Government Research Reports written by and published by . This book was released on 1963 with total page 768 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book U S Government Research Reports written by and published by . This book was released on 1963 with total page 1322 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book AIAA 70 200 AIAA 70 238 With omissions in numbering written by and published by . This book was released on 1970 with total page 540 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Techniques for Measurement of Dynamic Stability Derivatives in Ground Test Facilities written by Clarence John Schueler and published by . This book was released on 1967 with total page 242 pages. Available in PDF, EPUB and Kindle. Book excerpt: Some of the techniques in current use for measuring dynamic stability derivatives in wind tunnels are described, with emphasis given to the important features of balance system design, data reduction methods, instrumentation and typical balance systems. The use of gas bearings for dynamic stability and roll damping balances is treated and a three-degree-of-freedom balance system employing a spherical gas bearing is described. (Author).

Download or read book Bibliography of Scientific and Industrial Reports written by and published by . This book was released on 1963 with total page 1318 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book CFD Wing pylon finned Store Mutual Interference Wind Tunnel Experiment written by E. Rolland Heim and published by . This book was released on 1991 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Force and Moment Tests excluding Drag at Mach Number 2 58 on Three fin and Four fin Models of the Skylark High Altitude Research Vehicle written by D. F. Morrison and published by . This book was released on 1962 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigation of the Aerodynamic Characteristics of Five Forebody Models at High Angles of Attack at Mach Numbers from 0 25 to 2 written by and published by . This book was released on 1975 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigation of Three Axisymmetric Cowls of Different Lengths at Mach Numbers from 0 60 to 0 92 written by Richard J. Re and published by . This book was released on 1993 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Magnus Testing of a Canted Fin Or Self rotating Configuration written by Anders S. Platou and published by . This book was released on 1971 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A source of error in the wind tunnel measurement of Magnus forces and moments on a self-rotating configuration has been detected, and means of overcoming the error are presented. The error is due to a normal force interaction brought about by the roll of the angle of attack plane which in turn is due to a small yaw angle of the model at zero angle of attack. The error is not a balance interaction error. The error can completely mask the true Magnus characteristics and can lead the experimenter to wrong conclusions. Although a computed correction may be made to existing data, the best method of eliminating the error is to obtain balance readings with and without spin at each angle of attack of interest.

Download or read book Wind Tunnel Test Techniques written by Colin Britcher and published by Academic Press. This book was released on 2023-10-20 with total page 672 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind Tunnel Test Techniques: Design and Use at Low and High Speeds with Statistical Engineering Applications provides an up-to-date treatment of the topic. Beginning with a brief history of wind tunnels and its types and uses, the book goes on to cover subsonic, supersonic and hypersonic wind tunnel design and construction, calibration, boundary corrections, flow quality assessment, pressure surveys, and dynamic testing. It also focuses on wind tunnel facilities, making it useful for both the designer and operator. Engineers and graduate students in aerospace, automotive and similar programs will find this book useful in their work with experimental aerodynamics, gas dynamics, facility design and performance. - Deals with a broad range of flow speeds in wind tunnels, from low speed to high speed - Provides a discussion of similarity laws as well as material on statistical analysis - Includes coverage on facility-to-facility and facility-to-CFD correlation - Presents advanced topics such as cryogenic wind tunnels, ground simulation in automotive testing, and propulsion testing

Download or read book Longitudinal Airplane Dynamics Wind Tunnel Test Equipment written by O. B. Tufts and published by . This book was released on 1955 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigation of Effect of Yaw on Lateral stability Characteristics written by Isidore G. Recant and published by . This book was released on 1942 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.

Download or read book Wind Tunnel Investigation of the Effects of Surface Porosity and Vertical Tail Placement on Slender Wing Vortex Flow Aerodynamics at Supersonic Speeds written by Gary E. Erickson and published by BiblioGov. This book was released on 2013-07 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel experiment was conducted in the NASA Langley Research Center (LaRC) Unitary Plan Wind Tunnel (UPWT) to determine the effects of passive surface porosity and vertical tail placement on vortex flow development and interactions about a general research fighter configuration at supersonic speeds. Optical flow measurement and flow visualization techniques were used that featured pressure sensitive paint (PSP), laser vapor screen (LVS), and schlieren, These techniques were combined with conventional electronically-scanned pressure (ESP) and six-component force and moment measurements to quantify and to visualize the effects of flow-through porosity applied to a wing leading edge extension (LEX) and the placement of centerline and twin vertical tails on the vortex-dominated flow field of a 65 cropped delta wing model. Test results were obtained at free-stream Mach numbers of 1.6, 1.8, and 2.1 and a Reynolds number per foot of 2.0 million. LEX porosity promoted a wing vortex-dominated flow field as a result of a diffusion and weakening of the LEX vortex. The redistribution of the vortex-induced suction pressures contributed to large nose-down pitching moment increments but did not significantly affect the vortex-induced lift. The trends associated with LEX porosity were unaffected by vertical tail placement. The centerline tail configuration generally provided more stable rolling moments and yawing moments compared to the twin wing-mounted vertical tails. The strength of a complex system of shock waves between the twin tails was reduced by LEX porosity.