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 Full scale Wind tunnel Tests of a Small Unpowered Jet Aircraft with a T Tail written by Paul T. Soderman and published by . This book was released on 1971 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.

Download or read book Wind tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing fuselage Combination Having a Triangular Wing of Aspect Ratio 4 written by Paul G. Fournier and published by . This book was released on 1953 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results presented in the present paper are part of a program conducted to investigate the effect of wing plan form on the aerodynamic characteristics in pitch, in sideslip, and during steady roll. This paper presents the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4, a leading-edge sweep of angle of 45 degrees, and with an NACA 65A006 airfoil section parallel to the plane of symmetry.

Download or read book Wind tunnel Investigation at Mach Numbers from 0 50 to 1 29 of an Unswept Tapered Wing of Aspect Ratio 2 67 with Leading and Trailing edge Flaps Flaps Deflected in Combination written by Louis S. Stivers and published by . This book was released on 1951 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic characteristics of an unswept wing having an aspect ratio of 2.67, a taper ratio of 0.5, and employing full-span, 25-percent-chord, plain, leading- and trailing-edge flaps have been determined from wind-tunnel tests of a semispan model. Sections of the wing were 8-percent chord thick from the 25- to the 75-percent-chord points tapering to sharp leading and trailing edges. The data were obtained for a range of angles of attack from -3 to 12 degrees and for ranges of leading-edge-flap deflection from -20 to 10 degrees and a trailing-edge-flap deflection from 0 to 60 degrees. The Mach numbers ranged from about 0.50 to 0.95 and from 1.09 to 1.29 with corresponding Reynolds numbers varying from about 940,000 to 1,270,000.

Download or read book Blockage Study of a 1 16 scale B 1 Inlet Model in the 1 ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility written by C. F. Anderson and published by . This book was released on 1972 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 1-ft Aerodynamic Wind Tunnels (1T and 1S) of the Propulsion Wind Tunnel Facility to obtain estimates of the performance available for the full-scale B-1 inlet/engine tests in the 16-ft Propulsion Wind Tunnels (16T and 16S). Data were obtained with two nacelle configurations and four wing configurations. The maximum test section blockage was 17 percent. Data were obtained at Mach numbers from 0.55 to 1.30 and from 1.71 to 2.30. The tunnel performance for each configuration was evaluated relative to the others and with regard to the capabilities of the 16-ft tunnels. The results of these tests indicate that the available tunnel performance is significantly compromised with the nacelle configuration which has been selected for the full-scale test. The maximum Mach number estimated to be available for the full-scale test in Tunnel 16T is 1.0. To obtain a full range of engine operating points, however, testing should be restricted to M

Download or read book Wind tunnel Investigation at Mach Numbers from 0 50 to 1 29 of an Unswept Tapered Wing of Aspect Ratio 2 67 with Leading and Trailing edge Flaps Trailing edge Flaps Deflected written by Louis S. Stivers and published by . This book was released on 1950 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic characteristics of an unswept wing having an aspect ratio of 2.67, taper ratio of 0.5, and employing full-span, 25-percent chord, plain, trailing-edge flaps, have been determined from wind-tunnel tests of a semispan model. Sections of the wing model were 0.08 chord thick from the 0.25- to the 0.75-chord points, and tapered to sharp leading and trailing edges. The data were obtained for a range of angles of attack from -3 to 12 degrees and for a range of trailing-edge-flap deflections from -10 to 60 degrees at Mach numbers from about 0.50 to 0.98 and from 1.09 to 1.29. The Reynolds number varied from about 940,000 to 1,270,000. Whenever feasible the experimental results have been compared with theory.

Download or read book Low speed Wind tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing written by Arvid L. Keith and published by . This book was released on 1950 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.

Download or read book Wind tunnel Investigation at Mach Numbers from 0 50 to 1 29 of an All movable Triangular Wing of Aspect Ratio 4 Alone and with a Body written by Louis S. Stivers and published by . This book was released on 1950 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of an all-movable, triangular-plan-form wing alone and with a body have been determined from semispan model tests. The wing had an aspect ratio of 4 and had doubly symmetrical double-wedge sections with maximum thickness-chord ratios of 0.08 in the stream-wise direction. The experimental data were obtained at Mach numbers from 0.50 to about 0.98 and from 1.09 to 1.29 with corresponding Reynolds numbers varying from about 800,000 to 1,100,000. Calculated characteristics were compared with the corresponding experimental results.

Download or read book Tests of a Small scale NACA Submerged Inlet at Transonic Mach Numbers written by L. Stewart Rolls and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.

Download or read book Investigation of the NACA 4 3 08 03 Two blade Propeller at Forward Mach Numbers to 0 925 written by James B. Delano and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the NACA-4-(3)(08)-03 two-blade propeller has been made in the Langley 8-foot high-speed tunnel for blade angles of 55, 60, and 65 degrees at Mach numbers up to 0.925. Comparison of the force-test measurements obtained for the NACA-4-(3)(08)-03 two-blade propeller with those previously obtained for the NACA-4-(5)(08)-03 two-blade propeller indicates that the differences in design lift coefficient were insufficient to produce appreciable changes in maximum efficiency over the range of blade angle and Mach number investigated.

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 Investigation of the Aerodynamic Characteristics in Pitch of Wing fuselage Combinations at High Subsonic Speeds written by Thomas J. King and published by . This book was released on 1956 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results presented in the present paper represent a continuation of a research program conducted in the Langley high-speed 7- by 10-foot tunnel to investigate the aerodynamic characteristics in pitch, sideslip, and steady roll of model configurations having variations in the wing geometric parameters. Presented herein are the aerodynamic characteristics in pitch of wing-fuselage combinations with wings having an aspect ratio of 4, a sweepback angle of 45 degrees, end taper ratios of 0.3, 0.6,and 1.0. The Mach number range was from 0.40 to about 0.95 and the Reynolds number range was from 2,000,000 to 3,000,000.

Download or read book Aerodynamic Characteristics of a Leading edge Slat on a 35 Degree Swept back Wing for Mach Numbers from 0 30 to 0 88 written by John A. Kelly and published by . This book was released on 1951 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The data presented in this report were obtained by North American Aviation, Inc., from an investigation conducted in the Southern California Cooperative Wind Tunnel. Tests were made over a range of Mach numbers from 0.300 to 0.883 to determine the aerodynamic characteristics of a semispan model of a 35 degree swept-back wing equipped with a leading-edge slat and to gain additional knowledge of the aerodynamic loads and automatic operation of the slat. Lift, drag, and pitching-moment characteristics of a model wing in the presence of a fuselage were measured as well as pressures acting on the slat in the retracted and the full-open positions. The pressure data were analyzed to ascertain the opening characteristics of the slat for two possible circular-arc slat tracks which could be used for automatic operation of the slat.

Download or read book Low Speed Wind Tunnel Testing written by Jewel B. Barlow and published by John Wiley & Sons. This book was released on 1999-02-22 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: A brand-new edition of the classic guide on low-speed wind tunnel testing While great advances in theoretical and computational methods have been made in recent years, low-speed wind tunnel testing remains essential for obtaining the full range of data needed to guide detailed design decisions for many practical engineering problems. This long-awaited Third Edition of William H. Rae, Jr.'s landmark reference brings together essential information on all aspects of low-speed wind tunnel design, analysis, testing, and instrumentation in one easy-to-use resource. Written by authors who are among the most respected wind tunnel engineers in the world, this edition has been updated to address current topics and applications, and includes coverage of digital electronics, new instrumentation, video and photographic methods, pressure-sensitive paint, and liquid crystal-based measurement methods. The book is organized for quick access to topics of interest, and examines basic test techniques and objectives of modeling and testing aircraft designs in low-speed wind tunnels, as well as applications to fluid motion analysis, automobiles, marine vessels, buildings, bridges, and other structures subject to wind loading. Supplemented with real-world examples throughout, Low-Speed Wind Tunnel Testing, Third Edition is an indispensable resource for aerospace engineering students and professionals, engineers and researchers in the automotive industries, wind tunnel designers, architects, and others who need to get the most from low-speed wind tunnel technology and experiments in their work.

Download or read book Investigation of the NACA 4 4 06 04 Two blade Propeller at Forward Mach Numbers to 0 925 written by James B. Delano and published by . This book was released on 1949 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Investigations of the NACA-4-(4)(06)-04 two-blade propeller (design thickness, 0.06 at 0.7-radius station) have been made in the Langley 8-foot high-speed wind tunnel for blade angles from 20 to 70 degrees for forward Mach number up to 0.925.

Download or read book Wind Tunnel Tests of Shrouded Propellers at Mach Numbers from 0 to 0 60 written by Ronald M. Grose and published by . This book was released on 1958 with total page 412 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigations on Wings with and Without Sweepback at High Subsonic Speeds written by Jakob Ackeret and published by . This book was released on 1951 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Drag tests at zero lift have been made at Mach numbers from 0.7 to approximately 0.95 in the high speed wind tunnel of the Institute of Aerodynamics, ETH, Zurich, on a group of untapered wings of aspect ratio 3.25, having sweep angles of 0 degree and 35 degrees. For each sweep angle, a series of geometrically similar models was tested at a constant Reynolds number to provide a verification of computed tunnel blocking corrections. Tests were also made for wings having thickness ratios of 0.09 and 0.12 and the results compared with results predicted by von Karman's similarity law.