Download or read book Comparisons of In flight F 111A Inlet Performance for On and Off scheduled Inlet Geometry at Mach Numbers of 0 68 to 2 18 written by Richard A. Martin and published by . This book was released on 1971 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: In-flight F-111 data on total and static pressure from left inlet during automatically scheduled and manually controlled off-schedule positioning of spike at Mach 0.68 to 2.18.
Download or read book Comparisons of In flight F 111A Inlet Performance for On and Off scheduled Inlet Geometry at Mach Numbers Pf 0 68 to 2 18 written by Richard A. Martin and published by . This book was released on 1971 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Comparisons of In flight F 111A Inlet Performance for On and Off scheduled Inlet Geometry at Mach Numbers of 0 68 to 2 18 written by Richard A. Martin and published by . This book was released on 1971 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1971 with total page 450 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Documentation of the Phase III 0 192 scale Northrop McDonnell Douglas F 18 Inlet Performance Test at Mach Numbers 0 to 1 55 written by Jimmy Walker and published by . This book was released on 1978 with total page 222 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flight determined Characteristics of an Air Intake System on an F 111A Airplane written by Donald L. Hughes and published by . This book was released on 1972 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of a Large scale Two dimensional Mixed compression Inlet System written by Norman D. Wong and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: A large-scale, variable-geometry inlet model with a design Mach number of 3.0 was tested at Mach numbers from 1.55 to 3.2. Variable features of the inlet for off-design operation are an adjustable-height ramp system and a translating cowl. This report presents experimental results for a diffuser and boundary-layer bleed configuration which was optimized at the design Mach number. Overall performance was high with throat-mounted vortex generators, which were effective in reducing flow distortion in the subsonic diffuser at the higher Mach numbers.
Download or read book An Investigation of Two Variations of the Gas Generator Method to Calculate the Thrust of the Afterburning Turbofan Engines Installed in an F 111A Airplane written by Frank W. Burcham and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Installed F A 18 Inlet Flow Calculations at 30 Degrees Angle Of Attack A Comparative Study written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-10-29 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: NASA Lewis is currently engaged in a research effort as a team member of the High Alpha Technology Program (HATP) within NASA. This program utilizes a specially equipped F/A-18, the High Alpha Research Vehicle (HARV), in an ambitious effort to improve the maneuverability of high-performance military aircraft at low subsonic speed, high angle of attack conditions. The overall objective of the Lewis effort is to develop inlet technology that will ensure efficient airflow delivery to the engine during these maneuvers. One part of the Lewis approach utilizes computational fluid dynamics codes to predict the installed performance of inlets for these highly maneuverable aircraft. Full Navier-Stokes (FNS) calculations on the installed F/A-18 inlet at 30 degrees angle of attack, 0 degrees yaw, and a freestream Mach number of 0.2 have been obtained in this study using an algebraic turbulence model with two grids (original and revised). Results obtained with the original grid were used to determine where further grid refinements and additional geometry were needed. In order to account properly for the external effects, the forebody, leading edge extension (LEX), ramp, and wing were included with inlet geometry. In the original grid, the diverter, LEX slot, and leading edge flap were not included due to insufficient geometry definition, but were included in a revised grid. In addition, a thin-layer Navier-Stokes (TLNS) code is used with the revised grid and the numerical results are compared to those obtained with the FNS code. The TLNS code was used to evaluate the effects on the solution using a code with more recent CFD developments such as upwinding with TVD schemes versus central differencing with artificial dissipation. The calculations are compared to a limited amount of available experimental data. The predicted forebody/fuselage surface static pressures compared well with data of all solutions. The predicted trajectory of the vortex generated under the LEX was differe...
Download or read book Results of 0 2 Scale B 1 Production Inlet Development and Verification Tests at Subsonic and Supersonic Mach Numbers written by and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for a wind tunnel investigation of the 0.2- scale B-1 aircraft inlet/forebody model during which a production version of the inlet configuration was defined and the performance characteristics verified. The test was conducted at Mach numbers from 0 to 2.3, at angles of attack from - 2 to 13 deg, and at yaw angles from -6 to 6 deg. Performance data are presented primarily in the form of engine-face total-pressure recovery, turbulence index, and various distortion indices as a function of engine-face mass-flow ratio. For the development test phase, results are given that show the effects of reducing the inlet diffuser ramp length, varying the inlet cowl lip contours, changing the inlet bleed porosities, and reducing the inlet bleed discharge area. The performance characteristics of the selected inlet configuration are documented over the Mach number range with inlet geometry as controlled by the individual inlet control sensor schedules as well as by a free-stream Mach number schedule. The effects of control system errors and the aircraft takeoff inlet performance characteristics are also presented.
Download or read book Performance of a 1 6 scale F 111A Inlet at Transonic and Supersonic Mach Numbers written by James W. Huffman and published by . This book was released on 1967 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Steady state and Dynamic Pressure Phenomena in the Propulsion System of an F 111A Airplane written by Frank W. Burcham and published by . This book was released on 1973 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight tests were conducted with two F-111A airplanes to study the effects of steady-state and dynamic pressure phenomena on the propulsion system. Analysis of over 100 engine compressor stalls revealed that the stalls were caused by high levels of instantaneous distortion. In 73 percent of these stalls, the instantaneous circumferential distortion parameter, k sub theta, exhibited a peak just prior to stall higher than any previous peak. The K sub theta parameter was a better indicator of stall than the distortion factor, k sub d, and the maximum-minus-minimum distortion parameter, d, was poor indicator of stall. Inlet duct resonance occurred in both F-111A airplanes and is believed to have been caused by oscillations of the normal shock wave from an internal to an external position. The inlet performance of the two airplanes was similar in terms of pressure recovery, distortion, and turbulence, and there was good agreement between flight and wind-tunnel data up to a Mach number of approximately 1.8.
Download or read book Inlet Performance Characteristics of a Generalized 1 4 scale Tactical Aircraft Models at Transonic and Supersonic Mach Numbers written by R. F. Lauer (Jr.) and published by . This book was released on 1971 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Force Balance Determination of Inlet Performance for Advanced Vehicle Applications to Orbital Velocities Using Internal Drag Measurements written by Paul H. Kutschenreuter (Jr.) and published by . This book was released on 1963 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of the Full scale F 15 Inlet engine Compatibility Test at Subsonic and Supersonic Mach Numbers written by H. E. McDill and published by . This book was released on 1972 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of a 0 1 scale B 1 Inlet Model Test at Transonic and Supersonic Mach Numbers written by F. J. Graham and published by . This book was released on 1971 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented of a wind tunnel investigation of a 0.1-scale model of the left-hand dual inlet air induction system of the B-1 aircraft. The test was conducted from Mach number 0.55 to 2.2 over an angle-of-attack range from -4 to 13 deg and yaw angles of -8 to 5 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion, and turbulence index is presented as a function of inlet mass-flow ratios for various inlet geometries and model attitudes. The total-pressure recovery of the mixed-compression inlet was very good, but the total-pressure distortion at critical massflow ratios was higher than normally desired for satisfactory turbine engine operation. Best performance was realized with ramp and throat height schedules determined from previous testing. Effects of angle of attack and yaw were seen as general sidewash effects. The addition of canard-type fins had negligible effect on inlet performance. (Author).
Download or read book 0 2 scale B 1 External compression Inlet Verification Model Test at Transonic and Supersonic Mach Numbers written by R. C. German and published by . This book was released on 1974 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt:
