Aeropulsive Characteristics at Mach Numbers Up to 2.2 of Axisymmetric and Nonaxisymmetric Nozzles Installed on an F-18 Model PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Aeropulsive Characteristics at Mach Numbers Up to 2.2 of Axisymmetric and Nonaxisymmetric Nozzles Installed on an F-18 Model PDF full book. Access full book title Aeropulsive Characteristics at Mach Numbers Up to 2.2 of Axisymmetric and Nonaxisymmetric Nozzles Installed on an F-18 Model by Francis J. Capone. Download full books in PDF and EPUB format.
Author: Francis J. Capone Publisher: ISBN: Category : Jet nozzles Languages : en Pages : 84
Book Description
An investigation to determine the aeropropulsive characteristics of nonaxisymmetric nozzles on an F-18 jet effects model was conducted in the Langley 16-foot transonic tunnel and the AEDC 16-foot supersonic wind tunnel. The performance of a two dimensional convergent-divergent nozzle, a single expansion ramp nozzle, and a wedge nozzle was compared with that of the baseline axisymmetric nozzle. Test data were obtained at static conditions and at Mach numbers from 0.60 to 2.20 at an angle of attack of 0 deg. Nozzle pressure ratio was varied from jet-off to about 20.
Author: Francis J. Capone Publisher: ISBN: Category : Jet nozzles Languages : en Pages : 84
Book Description
An investigation to determine the aeropropulsive characteristics of nonaxisymmetric nozzles on an F-18 jet effects model was conducted in the Langley 16-foot transonic tunnel and the AEDC 16-foot supersonic wind tunnel. The performance of a two dimensional convergent-divergent nozzle, a single expansion ramp nozzle, and a wedge nozzle was compared with that of the baseline axisymmetric nozzle. Test data were obtained at static conditions and at Mach numbers from 0.60 to 2.20 at an angle of attack of 0 deg. Nozzle pressure ratio was varied from jet-off to about 20.
Author: Kalman J. Grunwald Publisher: ISBN: Category : Buffeting (Aerodynamics) Languages : en Pages : 148
Book Description
A series of force tests was conducted on unpowered, high-speed ground-vehicle model configurations to provide information on shapes of this type very near the ground. Of particular interest were the crosswind effects on the aerodynamic forces and moments of the six models tested. These tests were conducted over the moving-belt ground plane in the 17-foot (5.18-m) test section of the Langley 300-MPH 7-by 10-foot tunnel at free-stream dynamic pressure values of 10 lb/ft2 (478.8 N/m2). The results indicate that the half-circle configuration is desirable because of the low rolling moments it experienced; however, it did have higher lift values than the other configurations and, from a utility standpoint, could be impractical. The half-circle configurations with extended sides may make good compromise configurations. All the ground-simulation techniques employed -moving ground belt, fixed ground belt, and image model -gave reasonable representations of the overall aerodynamic trends.
Author: William H. Phillips Publisher: ISBN: Category : Rolling (Aerodynamics) Languages : en Pages : 44
Book Description
An attempt has been made to determine the importance of rolling performance and other factors in the design of an interceptor which uses collision-course tactics. A graphical method is presented for simple visualization of attack situations. By means of diagrams showing vectoring limits, that is, the ranges of interceptor position and heading from which attacks may be successfully completed, the relative importance of rolling performance and normal-acceleration capability in determining the success of attacks is illustrated. The results indicate that the reduction in success of attacks due to reduced rolling performance (within the limits generally acceptable from the pilots' standpoint) is very small, whereas the benefits due to substantially increasing the normal-acceleration capability are large. Additional brief analyses show that the optimum speed for initiating a head-on attack is often that corresponding to the upper left-hand corner of the V-g diagram. In these cases, increasing speed beyond this point for given values of normal acceleration and radar range rapidly decreases the width of the region from which successful attacks can be initiated. On the other hand, if the radar range is increased with a variation somewhere between the first and second power of the interceptor speed, the linear dimensions of the region from which successful attacks can be initiated vary as the square of the interceptor speed.
Author: Francis J. Capone
Author: Francis J. Capone
Author: Ronald D. Brown
Author: Langley Research Center
Author: James J. Adams
Author: Kalman J. Grunwald
Author: Lloyd S. Jernell
Author: W. Frank Staylor
Author: Nancy Jane Cyrus
Author: William H. Phillips
Author: C. W. Chiang