Download or read book Aerodynamic Characteristics in Pitch Including Effects of Horizontal tail Negative Dihedral Angle of a 0 048 scale Model of a Horizontal attitude VTOL Airplane at Transonic Speeds written by Walter B. Olstad and published by . This book was released on 1960 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1966 with total page 1348 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45 Sweptback wing Airplane Model with Various Vertical Locations of the Wing and Horizontal Tail written by M. Leroy Spearman and published by . This book was released on 1955 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a 1 4 inch Scale Model a Tilt wing VTOL Aircraft at High Angles of Wing Incidence written by Louis P. Tosti and published by . This book was released on 1960 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45 Degree Sweptback wing Airplane Model with Various Vertical Locations of the Wing and Horizontal Tail Effect of Wing Location and Geometric Dihedral for the Wing body Combination M written by M. Leroy Spearman and published by . This book was released on 1955 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Horizontal tail Height on Aerodynamic Characteristics of a Transport Model with a Variable sweep Warped Wing written by and published by . This book was released on 1965 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effects of Static Margin and Rotational Damping in Pitch on the Longitudinal Stability Characteristics of an Airplane as Determined by Tests of a Model in the NACA Free flight Tunnel written by John P. Campbell and published by . This book was released on 1944 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rotational damping in pitch was varied over a wide range by using horizontal tails that varied in area from 0 to 24 percent of the wing area. A range of static margins from 2 to 16 percent of the mean aerodynamic chord was covered in the tests. For each test condition the model was flown and the longitudinal steadiness characteristics were noted. It was found in the investigation that longitudinal steadiness was affected to a much greater extent by changes in static margin than by changes in rotational damping. The best longitudinal steadiness was noted at large values of static margin. For all values of rotational damping, the steadiness of the model decreased as the static margin was reduced. The model was especially unsteady at low values of static margin (0.03 or less). Reduction in rotational damping had little effect on longitudinal steadiness, except that with low values of static margin (0.03 or less) the longitudinal divergences were sometimes more violent with the tailless (low rotational damping) condition.
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 Effect of Horizontal tail Location on Low speed Static Longitudinal Stability and Damping in Pitch of a Model Having 45 Sweptback Wing and Tail Surfaces written by Jacob H. Lichtenstein and published by . This book was released on 1951 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the low-speed static longitudinal stability and steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees.
Download or read book Aerodynamic Characteristics in Pitch at a Mach Number of 1 97 of Two Variable wing Sweep V STOL Configurations with Outboard Wing Panels Swept Back 75 Deg written by and published by . This book was released on 1960 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Static Lateral Characteristics at High Subsonic Speeds of a Complete Airplane Model with a Highly Tapered Wing Having the 0 80 Chord Line Unswept and with Several Tail Configuration written by Kenneth W. Goodson and published by . This book was released on 1961 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made at high subsonic speeds of a complete model having a highly tapered wing and several tail configurations. The aspect-ratio-3.50 wing had a taper of 0.067 and an unswept 0.80 chord line. The complete model was tested with a wing-chord-plane tail, a T-tail, and a biplane tail (combined T-tail and wing-chord-plane tail). The model was tested in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92 over a range of angle of attack of about ±20° and a range of sideslip of -15° to 13°. Some data were obtained with the horizontal stabilizer deflected. A few tests were also made with the wing tips clipped to an aspect ratio of 3.00.
Download or read book Effects of Horizontal tail Position and a Wing Leading edge Modification Consisting of a Full span Flap and a Partial span Chord extension on the Aerodynamic Characteristics in Pitch at High Subsonic Speeds of a Model with a 45 Degree Sweptback Wing written by William D. Morrison and published by . This book was released on 1957 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the range of horizontal-tail positions investigated, the most desirable pitching-moment characteristics obtained, either with or without the wing modification, were with the lowest tail position (0.139 semispan below wing chord plane extended). The wing modification provided considerable improvement in pitching-moment characteristics for tail positions above the chord plane extended. The improvements obtained at Mach numbers near 0.90 were much smaller, however, than those obtained at lower Mach numbers.
Download or read book Effect of Horizontal tail Size and Tail Length on Low speed Static Longitudinal Stability and Damping in Pitch of a Model Having 45 Sweptback Wing and Tail Surfaces written by Jacob H. Lichtenstein and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel results of the effects of horizontal-tail size and length on the low-speed static longitudinal stability and the steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees and aspect ratios of 4 are presented.
Download or read book Effects of Vertical tail Size and a Ventral Fin on the Static Lateral and Directional Stability Derivatives of a 0 048 scale Model of a Horizontal attitude VTOL Airplane at Transonic Speeds written by and published by . This book was released on 1960 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Aerodynamic Characteristics in Pitch and Sideslip of a 45 Degree Sweptback wing Airplane Model with Various Vertical Locations of Wing and Horizontal Tail written by M. Leroy Spearman and published by . This book was released on 1956 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of various vertical locations of the wing and horizontal tail on the aerodynamic characteristics in pitch of a supersonic airplane configuration at a Mach number of 2.01. The model is equipped with a wing and horizontal tail, each having a 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 with NACA 65A004 airfoil sections, whereas the horizontal tail had a taper ratio of 0.6 with NACA 65A006 airfoil sections.
Download or read book Effects of Vertical Location of Wing and Horizontal Tail on the Aerodynamic Characteristics in Pitch at Mach Numbers from 0 60 to 1 40 of an Airplane Configuration with an Unswept Wing written by Louis S. Stivers and published by . This book was released on 1957 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the effects of vertical location of an unswept wing and horizontal tail on the aerodynamic characteristics in pitch of a wing-body-tail combination. The wing had an aspect ratio of 3.09, a taper ratio of 0.39, and quarter-chord line swept back 11.5 degrees, and biconvex sections. Lift, drag, and pitching-moment coefficients were obtained at Mach numbers from 0.60 to 1.40 for angles of attack from -4 to approximately 13 degrees, with the boundary-layer transition on the model fixed and free. The Reynolds number of the tests was 1.5 million, based on the wing mean aerodynamic chord. The effects of Mach number on the experimental and calculated lift curve slopes, pitching-moment curve slopes, and contributions of the horizontal tail to the pitching-moment curve slopes are presented for the various wing and horizontal-tail locations.
Download or read book Determination of Lateral Stability Characteristics from Free flight Model Tests with Experimental Results on the Effects of Wing Vertical Position and Dihedral at Transonic Speeds written by Clarence L. Gillis and published by . This book was released on 1960 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
