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.
Download or read book Analysis of Wind tunnel Tests to a Mach Number of 0 90 of a Four engine Propeller driven Airplane Configuration Having a Wing with 40 degrees of Sweptback and an Aspect Ratio of 10 written by George G. Edwards and published by . This book was released on 1956 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of Wind tunnel Tests at Low Speeds of a Four engine Propeller driven Airplane Configuration Having a Wing with 40 Degrees of Sweepback written by George G. Edwards and published by . This book was released on 1954 with total page 137 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Buffeting Measurements on Two Wing End plate Airplane Model Configurations written by William B. Igoe and published by . This book was released on 1967 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Test Report Conventional Model Volume Iii High Speed mach written by GENERAL ELECTRIC CO CINCINNATI OHIO ADVANCED ENGINE AND TECHNOLOGY Dept and published by . This book was released on 1964 with total page 547 pages. Available in PDF, EPUB and Kindle. Book excerpt: The volume presents the results of high speed wind tunnel test of a one-eighth scale model of the U.S. Army XV-5A Lift Fan Research Aircraft. The tests were conducted at the David Taylor Model Basin 7 x 10 foot Transonic Wind Tunnel Facility. Conventional model force, pressure, and hinge moment data were obtained over a Mach number range of .40 to .90 and pitch and sideslip ranges of -4 to 15 degrees and -5 to +5 degrees respectively. The complete aircraft was the primary configuration tested, with the majority of the variations being in control surface and stabilizer settings. Tests were also conducted with the vertical and horizontal tail surfaces removed, with wing fan upper and lower surface strut fairings removed, and with engine duct pressure survey rake installed. (Author).
Download or read book Wind Tunnel Tests of an F 8 Airplane Model Equipped with an Oblique Wing written by and published by . This book was released on 1973 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Flight and Wind Tunnel Investigation of the Effect of Angle of attack Rate on Maximum Lift Coefficient written by Fox Conner and published by . This book was released on 1965 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind Tunnel Test of a 14 Percent Thick Oblique Wing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-04 with total page 436 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted at the ARC 11- by 11-Foot Transonic Wind Tunnel as part of the Oblique Wing Research Aircraft Program to study the aerodynamic performance and stability characteristics of a 0.087-scale model of an F-8 airplane fitted with an oblique wing designed by Rockwell International. The 10.3 aspect ratio, straight-tapered wing of 0.14 thickness/chord ratio was tested at two different mounting heights above the fuselage. Additional tests were conducted to assess low-speed behavior with and without flaps, aileron effectiveness at representative flight conditions, and transonic drag divergence with 0 degree wing sweep. Longitudinal stability data were obtained at sweep angles of 0, 30, 45, 60, and 65 degrees, at Mach numbers ranging from 0.25 to 1.40. Test Reynolds numbers varied from 3.2 to 6.6 x 10 exp 6/ft. and angle of attack ranged from -5 to +18 degrees. Most data were taken at zero sideslip, but a few runs were at sideslip angles of +/- 5 degrees. The raised wing position proved detrimental overall, although side force and yawing moment were reduced at some conditions. Maximum lift coefficient with the flaps deflected was found to fall short of the value predicted in the preliminary design document. The performance and trim characteristics of the present wing are generally inferior to those obtained for a previously tested wing designed at ARC. Kennelly, Robert A., Jr. and Kroo, Ilan M. and Strong, James M. and Carmichael, Ralph L. Ames Research Center NASA-TM-102230, A-89236, NAS 1.15:102230 RTOP 533-06-01...
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 Aerodynamic Hysteresis Phenomenon on the F 4 Aircraft and Its Effects on Aircraft Motion written by J. F. Herman and published by . This book was released on 1980 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel test program and an analytical study were conducted to investigate aerodynamic hysteresis phenomena on the F-4 aircraft. The wind tunnel test was conducted in the Arnold Engineering Development Center (AEDC) Aerodynamic Wind Tunnel (4T) to investigate the source of aerodynamic hysteresis in static aerodynamic data. The wind tunnel test also provided data that were used in a motion simulation study of the effect of hysteresis on predicted aircraft motion. Static longitudinal lateral directional force and moment data and wing pressure data were obtained on a 0.5-scale model (without pylons or external stores) with various simulated leading-edge slats. These data include the effects of Mach number, angle of attack, model movement, and time dependence on the aerodynamic hysteresis characteristics. Data are presented for the Mach number range from 0.7 to 0.95 at angles of attack from -4 to 24 deg at zero deg sideslip angle and for sideslipe angles from -12 to 12 deg at angles of attack of 5, 10, 15, and 20 deg. Six-degrees-of-freedom motion simulation studies were used to assess the effect of hysteresis in the rolling-moment coefficient on the prediction of aircraft motion. Simulations of various flight maneuvers were conducted both with and without hysteresis in the aerodynamic data. (Author).
Download or read book Large scale Wind tunnel Tests of a Deflected Slipstream STOL Model with Wings of Various Aspect Ratios written by V. Robert Page and published by . This book was released on 1968 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Tests in the Ames 40 by 80 foot Wind Tunnel of an Airplane Configuration with an Aspect Ratio 4 Triangular Wing and an All movable Horizontal Tail Longitudinal Characteristics written by David Graham and published by . This book was released on 1951 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel and Analytical Investigation of Over the wing Propulsion air Frame Interferences for a Short haul Aircraft at Mach Numbers from 0 6 to 0 78 written by and published by . This book was released on 1977 with total page 252 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel flight Data Correlation u written by James A. Behal and published by . This book was released on 1971 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program was conducted to obtain data, both steady state and dynamic, from wind tunnel models and full scale flight tests of the RA-5C aircraft. Data were acquired on 0.228 and 0. 125 scale RA-5C inlet models and on a fully instrumented flight test RA-5C aircraft. Interim data reports presenting the data acquired during each test have been published. These data were utilized in this report to develop scaling techniques for correlating small scale model wind tunnel data with full scale flight data. Data presented include duct steady state operating characteristics and pressure distributions in the inlet and at the engine face. Dynamic data are presented in the form of engine face turbulence contour plots, radial turbulence distributions and selected spectral data functions. Data are presented for variations of angle of attack, angle of yaw, Reynolds number, ramp angle, secondary flow rates and inlet diverter width. Brief descriptions of the model and test methods are also presented.
Download or read book Wind Tunnel Tests on a 90 Degree Apex Delta Wing of Variable Aspect Ratio sweepback 36 8 Degrees Part I written by J. G. Ross and published by . This book was released on 1952 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Tests on a 90 apex Delta Wing of Variable Aspect Ratio sweepback 36 8 Part 1 by J G Ross R Mills and R C Lock Part 2 Measurements of Down wash and Effect of High Lift Devices by R C Lock J G Ross and P Meiklem written by Aeronautical Research Council and published by . This book was released on 1952 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Transonic wing Investigation in the Langley 8 foot High speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1 2 written by Maurice S. Cahn and published by . This book was released on 1951 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
