Download or read book High subsonic Damping in roll Characteristics of a Wing with the Quarter chord Line Swept Back 35 Degrees and with Aspect Ratio 3 and Taper Ratio 0 6 written by Boyd C. II. Myers and published by . This book was released on 1949 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Damping in pitch Characteristics at High Subsonic and Transonic Speeds of Four 35 Sweptback Wings written by William B. Kemp and published by . This book was released on 1953 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Mach Number and Sweep on the Damping in roll Characteristics of Wings of Aspect Ratio 4 written by Richard E. Kuhn and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, sweep angles of 3.6, 32.5, and 46.7 degrees at quarter-chord line, and with the NACA 65A006 section have been determined through the Mach number range from 0.4 to 0.91 and angle-of-attack range from 0 to 6.5 degrees in the Langley high-speed 7- by 10-foot tunnel by the free-roll method. The results indicated that the increase in magnitude of the damping-in-roll coefficient with Mach number and the decrease with sweep angle, at low angles of attack, agreed well with the theoretical variations. The damping coefficient increased markedly with angle of attack (in the test range) particularly at the higher Mach numbers investigated.

Download or read book Wind tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13 and at High Subsonic Mach Numbers Including a Semiempirical Method of Estimating the Rolling Derivatives written by James W. Wiggins and published by . This book was released on 1954 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.

Download or read book The Rolling Moment Due to Sideslip of Swept Wings at Subsonic and Transonic Speeds written by Edward C. Polhamus and published by . This book was released on 1955 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: A summary and analysis has been made of results obtained in a systematic research program concerned with the effects of wing sweep, aspect ratio, taper ratio, and dihedral on the rolling moment due to sideslip characteristics of wing-fuselage configurations up to Mach numbers of about 0.95. Other test results are presented to show trends of rolling moment due to sideslip with Mach number for a few wings in the transonic and supersonic speed range.

Download or read book Effects of Sweep on the Damping in roll Characteristics of Three Sweptback Wings Having an Aspect Ratio of 4 at Transonic Speeds written by Vernard E. Lockwood and published by . This book was released on 1950 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: The damping-in-roll characteristics of three wings having an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil section, and sweep angles of 0, 35, and 45 degrees have been determined through a Mach number range from 0.6 to 1.15 and an angle-of-attack range from 0 to approximately 7 degrees. The data were obtained from the Langley 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique.

Download or read book Theoretical Lift and Damping in Roll of Thin Sweptback Wings of Arbitrary Taper and Sweep at Supersonic Speeds written by Frank S. Malvestuto and published by . This book was released on 1949 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-roll derivative for given values of aspect ratio, taper ratio, Mach number, and leading edge sweep.

Download or read book A Simple Method of Estimating the Subsonic Lift and Damping in Roll of Sweptback Wings written by Edward C. Polhamus and published by . This book was released on 1949 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of modifying existing correction factors of lifting-surface theory to account approximately for the effects of sweep has been derived, and these factors have been applied to existing lifting-line theories for the lift and damping in roll of swept wings. A comparison with experimental data in the low-speed and low lift range indicated good agreement for wings of any plan form. If the Glauert-Prandtl transformation is used, the formulas obtained can be applied to swept wings at subsonic speeds below the critical speed.

Download or read book Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45 Swept wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail written by M. Leroy Spearman and published by . This book was released on 1957 with total page 34 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 wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.

Download or read book Damping in Roll of Models with 45 60 and 70 Delta Wings Determined at High Subsonic Transonic and Supersonic Speeds with Rocket powered Models written by E. Claude Sanders and published by . This book was released on 1952 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Subsonic Roll Damping of a Model with Swept back and Swept forward Wings written by and published by . This book was released on 1978 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Damping in roll Calculations for Slender Swept back Wings and Slender Wing body Combinations written by Harvard Lomax and published by . This book was released on 1949 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: The damping-in-roll parameter C(iota)(p) is calculated theoretically for triangular wings on cylindrical bodies and for a class of wings with sweptback plan forms. The analysis is based on the usual assumptions of linearized compressible-flow theory together with the added restrictions that at the free-stream Mach number M(omicron) the product of lM(omicron)(2) and the streamwise velocity gradient is small.

Download or read book Wind tunnel Investigation of the Effects of Steady Rolling on the Aerodynamic Loading Characteristics of a 45 Sweptback Wing at High Subsonic Speeds written by James W. Wiggins and published by . This book was released on 1954 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Damping in pitch Characteristics at High Subsonic and Transonic Speeds of Four 35 Degree Sweptback Wings written by William B. Jr Kemp and published by . This book was released on 1953 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Effect at High Subsonic Speeds of a Flap type Aileron on the Chordwise Pressure Distribution Near Midspan of a Tapered 35 Degree Sweptback Wing of Aspect Ratio 4 Having NACA 65A006 Airfoil Section written by Alexander D. Hammond and published by . This book was released on 1953 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Damping of Straight and 45 Degrees Swept Wings of Various Taper Ratios Determined at High Subsonic Transonic and Supersonic Speeds with Rocket powered Models written by E. Claude Jr Sanders and published by . This book was released on 1951 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Taper Ratio on the Low speed Rolling Stability Derivatives of Swept and Unswept Wings of Aspect Ratio 2 61 written by Jack D. Brewer and published by . This book was released on 1951 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of tests conducted in the 6-foot diameter rolling-flow test section of the Langley stability tunnel to determine the effects of varying taper ratio on the rolling and static stability characteristics of a swept wing are presented; results are also given for the effects of varying taper on an unswept wing and for the effects of sweep on a tapered wing. All the models were of aspect ratio 2.61 and had NACA 0012 sections normal to the quarter-chord line. Taper ratios of 1.00, 0.50, and 0.25 and sweep angles of 0 to 45 degrees were investigated.