Download or read book Transonic Longitudinal Aerodynamic Effects of Sweeping Up the Rear of the Fuselage of a Rocket propelled Airplane Model Having No Horizontal Tail written by James H. Parks and published by . This book was released on 1955 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1957 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1959 with total page 382 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Research Abstracts and Reclassification Notice written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 716 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A New Dimension Wallops Island Flight Test Range written by Joseph Adams Shortal and published by . This book was released on 1978 with total page 808 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Investigation of Aerodynamic Characteristics of a Swept wing Fighter airplane Model with Leading edge Droop in Combination with Outboard Chord extensions and Notches written by Charles F. Whitcomb and published by . This book was released on 1956 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.

Download or read book Longitudinal Aerodynamic Characteristics of a Model Airplane Configuration Equipped with a Scaled X 1 Airplane Wing written by James H. Parks and published by . This book was released on 1952 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Longitudinal Aerodynamic Characteristics of a Variable sweep Tactical fighter Model with Wing Sweeps of 25 65 85 and 160 Degrees written by and published by . This book was released on 1962 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Subsonic Static Aerodynamic Characteristics of an Airplane Model Having a Triangular Wing of Aspect Ratio 3 written by Howard F. Savage and published by . This book was released on 1957 with total page 662 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted to determine the effects of vertical-tail location and size on the subsonic aerodynamic characteristics of a model having a triangular wing. The wing had an aspect ratio of 3, an NACA 0003.5-63 section in the streamwise direction, and plain, trailing-edge ailerons. The wing was attached to the fuselage in either a mid or high position and an unswept horizontal tail was located on the fuselage center line. Two vertical tails were tested which had areas of 26.7 or 20.3 percent of the wing area. Each vertical tail was equipped with a rudder and had a geometric aspect ratio of 1.5, a taper ratio of 0.16, and 54 degrees of sweepback of the leading edge. Each vertical tail was tested at two different tail lengths. The wind-tunnel tests were conducted at a Reynolds number of 2.5 milMon at Mach numbers from 0.25 to 0.95.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 0 3 and NACA 65A006 Airfoil Section written by Boyd C. Myers and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.

Download or read book Preliminary Flight Research on an All movable Horizontal Tail as a Longitudinal Control for Flight at High Mach Numbers written by Harold F. Kleckner and published by . This book was released on 1945 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The NACA is conducting flight tests of an all-movable horizontal tail installed on a Curtiss XP-42 airplane because of its possible advantages as a longitudinal control for flight at high Mach numbers. The results are presented for some preliminary tests in the low-speed range for which the tail was very closely balanced aerodynamically and a bobweight was used to obtain stable stick-force variations with speed and acceleration. For these tests, the tail was hinged at 0.24 chord and was tried with two arrangements of servotab control. The elevator control was found to be unsatisfactory with the control arrangements tested. Although there were sufficient variation of stick force with acceleration in steady turns and a stable stick-force variation with speed, the near-zero variation of stick force with stick deflection resulted in an extremely sensitive control that required continuous attention in order to avoid motions of the airplane due to inadvertent movements of the control stick. For subsequent tests, the servotabs are being connected as geared unbalancing tabs in order that more conventional elevator hinge-moment characteristics may be obtained. The expected advantages of the all-movable tail with a control system utilizing tabs would of course be limited to flight at Mach numbers below those for which severe compressibility effects are encountered on the tail itself. For higher Mach numbers, the all-movable tail would require an irreversible power-boost control in order to handle the large hinge-moment increases that are expected.

Download or read book The Effect on Stability and Control of a Pusher Propeller Behind Conventional Tail Surfaces as Determined by Tests of a Powered Model in the Free flight Tunnel written by John P. Campbell and published by . This book was released on 1943 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The effects on stability and control of a pusher propeller behind conventional horizontal and vertical tail surfaces have been determined in the NACA free-flight tunnel by tests of a 1/10-scale model of an NACA submerged-engine pusher airplane design. The investigation consisted of flight and balance tests at windmilling and high-power conditions with a partial-span Zap extensible flap extended and retracted. The effects of changes in vertical-tail area, horizontal-tail incidence, and center-of-gravity location were also determined.

Download or read book Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees Aspect Ratio 4 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.

Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Buffet Investigation at High Subsonic Speeds of Wing fuselage tail Combinations Having Sweptback Wings with NACA 64A Thickness Distributions Fences a Leading edge Extension and Body Contouring written by Fred B. Sutton and published by . This book was released on 1957 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made to determine the effect of wing fences, a wing leading-edge extension, changing wing sweepback angle from 40 to 45 and 50 degrees, fuselage contouring, and varying horizontal tail height upon the buffeting response of some typical airplane configurations employing sweptback wings with high aspect ratios. The tests were conducted through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million.

Download or read book Flight Studies of the Horizontal tail Loads Experienced by a Modern Pursuit Airplane in Abrupt Maneuvers written by Langley Aeronautical Laboratory and published by . This book was released on 1944 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Flight measurements were made on a modern pursuit airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of the fluctuating tail loads in accelerated stalls. The results indicated that, if the airplane were not stalled, a total up load of 5700 pounds would be experienced on the horizontal tail in an 8g pull-up and that, with power on, this load would be distributed unsymmetrically with about 800 pounds more up load on the left stabilizer than on the right. When stalling occurred there was an initial abrupt increase in the up tail load of the order of 100 percent of the previous load, which was followed by repeated load and stress variations due to tail buffeting. Under the condition of tail buffeting, the possibility of excessive stresses due to resonance was indicated.

Download or read book Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical tail load Characteristics of a Complete Model Having a Delta Wing written by Edward C. Polhamus and published by . This book was released on 1958 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.