Download or read book Effects of Spanwise Thickness Variation on the Transonic Aerodynamic Characteristics of Wings Having 35 Degrees of Sweepback Aspect Ratio 4 and Taper Ratio 0 60 written by William D. Morrison and published by . This book was released on 1951 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of a spanwise variation in thickness ratio on the aerodynamic characteristics of a wing having a plan form identical to that of a constant-percent thickness-ratio wing previously investigated as part of an extensive transonic research program. The wing with thickness variation had 35 degrees of sweepback, aspect ratio 4, and taper ratio 0.60, with airfoil section (parallel to the free stream) tapered from an NACA 65A006 section at root chord to an NACA 65A002 section at the tip chord. The test Mach number range was from 0.60 to 1.08 at Reynolds numbers of the order 0f 650,000.
Download or read book Effects of Spanwise Thickness Variation on the Aerodynamic Characteristics of 35 Degree and 45 Degree Sweptback Wings of Aspect Ratio 6 written by William D. Morrison and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An aerodynamic investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamics characteristics of wings having 35 and 45 degrees of sweep-back, aspect ratio 6, and taper ratio 0.60. The wings were tapered from NACA 65A009 airfoil sections at the root chord to NACA 65A003 airfoil sections at the tip chord. The test Mach number range was from 0.60 to 1.14 at a Reynolds number of the order of 500,000.
Download or read book An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47 Sweepback Aspect Ratio 3 5 and Taper Ratio 0 2 in the Slotted Test Section of the Langley 8 foot High speed Tunnel written by Ralph P. Bielat and published by . This book was released on 1951 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.
Download or read book Effects of Sweep and Thickness on the Static Longitudinal Aerodynamic Characteristics of a Series of Thin Low aspect ratio Highly Tapered Wings at Transonic Speeds written by Albert G. Few and published by . This book was released on 1954 with total page 107 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects on drag and lift-drag ratio of a variation in sweep angle from -14.03 degrees to 45 degrees with respect to the quarter-chord line for wings of 3-percent-chord thickness was found to be small in comparison to the effects of a variation in thickness from 2 percent chord to 4.5 percent chord for wings with 14.03 degree sweepback.
Download or read book Lift Pitching Moment and Span Load Characteristics of Wings at Low Speed as Affected by Variations of Sweep and Aspect Ratio written by Edward J. Hopkins and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0, 35, and 45 degrees. The wing span was decreased to give aspect ratios 6.8, 5.3, 4.2, 3.4, and 2.8. The effects of independent variations of sweep and aspect ratio on the lift, pitching-moment, and span-load characteristics of the wings are compared with the effects estimated by use of the Weissinger method.
Download or read book The Transonic Aerodynamic Characteristics of Structurally Related Wings of Low Aspect Ratio Having a Spanwise Variation in Thickness Ratio Transonic Bump Technique written by Joseph W. Cleary and published by . This book was released on 1954 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47 Degrees Sweepback Aspect Ratio 3 5 and Taper Ratio 0 2 in the Slotted Test Section of the Langley 8 foot High speed Tunnel written by Ralph P. Bielat and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.
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 Aerodynamic Characteristics at Transonic Speeds of a Wing Having a 45 Degree Sweep Aspect Ratio 8 Taper Ratio 0 45 and Airfoil Sections Varying from the NACA 63A010 Section at the Root to the NACA 63A006 Section at the Tip written by William D. Morrison and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley High-Speed 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing having a spanwise variation in thickness ratio. The wing investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio of 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. The test Mach number range was from 0.60 to 1.05 at Reynolds numbers of the order of 500,000.
Download or read book Transonic Wind tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing body Combination of Aspect Ratio 4 and Taper Ratio 0 6 written by Robert J. Platt and published by . This book was released on 1955 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.
Download or read book Aircraft written by and published by . This book was released on 1951 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degrees 35 Degrees 45 Degrees and 60 Degrees NACA 65A006 Airfoil Section Aspect Ratio 4 and Taper Ratio 0 6 in Combination with a Fuselage at High Subsonic Mach Numbers and at a Mach Number of 1 2 written by Arvo A. Luoma and published by . This book was released on 1951 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of an End Plate on the Aerodynamic Characteristics of a 20 55 Degree Sweptback Wing with an Aspect Ratio of 2 67 and a Taper Ratio of 0 5 written by James M. Watson and published by . This book was released on 1950 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation by the transonic-bump method conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effect of an end plate on the aerodynamic characteristics of a 20.55 degree sweptback wing with an aspect ratio of 2.67 and a taper ratio of 0.5 indicated that the end plate affect the aerodynamic characteristics of the wing at transonic Mach numbers in the same manner as has been observed for swept and unswept wings at low speeds.
Download or read book Effects of Three Spanwise Twist Variations on the Longitudinal Aerodynamic Characteristics of a Thin 45 Deg Sweptback Highly Tapered Wing at Transonic Speeds written by and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Aerodynamic Characteristics of a Wing Body Combination Having a 52 5 Deg Sweptback Wing of Aspect Ratio 3 with Conical Camber and Designed for a Mach Number of the Square Root of 2 written by William B. Igoe and published by . This book was released on 1961 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book THE TRANSONIC CHARACTERISTICS OF UNSWEPT WINGS HAVING ASPECT RATIOS OF 4 SPANWISE VARIATIONS IN THICKNESS RATIO AND VARIATIONS IN PLAN FORM TAPER TRANSONIC BUMP TECHNIQUE written by and published by . This book was released on 1954 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Aerodynamic Characteristics in Pitch of a W wing Having 60 Degree 48 Minutes Panel Sweep Aspect Ratio 3 5 and Taper Ratio 0 25 written by William D. Jr Morrison and published by . This book was released on 1953 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
