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Investigation Of The Effects Of Body Indentation And Of Wing Plan Form Modification On The Longitudinal Characteristics Of A 60 Degree Swept Wing Body Combination At Mach Numbers Of 141 161 And 201
Download Investigation Of The Effects Of Body Indentation And Of Wing Plan Form Modification On The Longitudinal Characteristics Of A 60 Degree Swept Wing Body Combination At Mach Numbers Of 141 161 And 201 full books in PDF, epub, and Kindle. Read online Investigation Of The Effects Of Body Indentation And Of Wing Plan Form Modification On The Longitudinal Characteristics Of A 60 Degree Swept Wing Body Combination At Mach Numbers Of 141 161 And 201 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Investigation of the Effects of Body Indentation and of Wing-plan-form Modification on the Longitudinal Characteristics of a 60 Degree Swept-wing Body Combination at Mach Numbers of 1.41, 1.61, and 2.01 by : John R. Jr Sevier
Download or read book Investigation of the Effects of Body Indentation and of Wing-plan-form Modification on the Longitudinal Characteristics of a 60 Degree Swept-wing Body Combination at Mach Numbers of 1.41, 1.61, and 2.01 written by John R. Jr Sevier and published by . This book was released on 1955 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 by : Royce L. McKinney
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 written by Royce L. McKinney and published by . This book was released on 1965 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63 by : Maurice O. Feryn
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63 written by Maurice O. Feryn and published by . This book was released on 1966 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Effect of Indentation on an M-plan-form-wing--body Combination at Transonic Speeds by : Donald L. Loving
Download or read book Investigation of the Effect of Indentation on an M-plan-form-wing--body Combination at Transonic Speeds written by Donald L. Loving and published by . This book was released on 1954 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of body indentation on the aerodynamic characteristics of an M-plan-form-wing-body combination has been investigated for angles of attack 0 to 12 percent at Mach numbers from 0.80 to 1.13 in the Langley 8-foot transonic tunnel. The Reynolds number of the investigation varied from 1,600,000 to 1,660,000. The M-wing with 45 degrees sweep angles was tested on a plain body and a body with an indentation that was 65 percent of that required for a Mach number of 1.0. A similar 45 degree sweptback wing was tested on a plain body to furnish basic comparison information.
Book Synopsis Investigation of the Effects of Body Camber and Body Indentation on the Longitudinal Characteristics of a 60 Degree Delta-wing-body Combination at a Mach Number of 1.61 by : John R. Sevier
Download or read book Investigation of the Effects of Body Camber and Body Indentation on the Longitudinal Characteristics of a 60 Degree Delta-wing-body Combination at a Mach Number of 1.61 written by John R. Sevier and published by . This book was released on 1956 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of body camber and body indentation on the longitudinal characteristics of a delta-wing-body combination at a Mach number of 1.61. In combination with a 3-percent-thick 60 degree delta wing, the following three bodies were tested: (1) a basic parabolic body (Sears-Haack), (2) a body indented so as to have an improved wing-body area distribution at a Mach number of 1.8, and (3) a body which was both indented and cambered.
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers from 1.70 to 4.63 by : Lloyd S. Jernell
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers from 1.70 to 4.63 written by Lloyd S. Jernell and published by . This book was released on 1965 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 by :
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 written by and published by . This book was released on 1965 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Summary and Analysis of Horizontal-tail Contribution to Longitudinal Stability of Swept-wing Airplanes at Low Speeds by : Robert H. Neely
Download or read book Summary and Analysis of Horizontal-tail Contribution to Longitudinal Stability of Swept-wing Airplanes at Low Speeds written by Robert H. Neely and published by . This book was released on 1959 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tail locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 105 and at Mach numbers less than 0.25.
Book Synopsis Some Effects of Tail Height and Wing Plan Form on the Static Longitudinal Stability Characteristics of a Small-scale Model at High Subsonic Speeds by : Albert G. Few
Download or read book Some Effects of Tail Height and Wing Plan Form on the Static Longitudinal Stability Characteristics of a Small-scale Model at High Subsonic Speeds written by Albert G. Few and published by . This book was released on 1954 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.
Book Synopsis An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence by : John A. Axelson
Download or read book An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence written by John A. Axelson and published by . This book was released on 1948 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability.
Book Synopsis Effects at Mach Numbers of 1.61 and 2.01 of Camber and Twist on the Aerodynamic Characteristics of Three Swept Wings Having the Same Planform by : Emma Jean Landrum
Download or read book Effects at Mach Numbers of 1.61 and 2.01 of Camber and Twist on the Aerodynamic Characteristics of Three Swept Wings Having the Same Planform written by Emma Jean Landrum and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Wing Planform Modification on Longitudinal Characteristics of a Variable-sweep M Wing by : Edward J. Ray
Download or read book Effect of Wing Planform Modification on Longitudinal Characteristics of a Variable-sweep M Wing written by Edward J. Ray and published by . This book was released on 1965 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the Influence of Body Size and Indentation Asymmetry on the Effectiveness of Body Indentation in Combination with a Cambered Wing by : James C. Patterson
Download or read book An Investigation of the Influence of Body Size and Indentation Asymmetry on the Effectiveness of Body Indentation in Combination with a Cambered Wing written by James C. Patterson and published by . This book was released on 1961 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Symmetrical Body Indentations Designed to Reduce the Transonic Zero-lift Wave Drag of a 45 Degree Swept Wing with an NACA 64A006 Section and with a Thickened Leading-edge Section by : George H. Holdaway
Download or read book Investigation of Symmetrical Body Indentations Designed to Reduce the Transonic Zero-lift Wave Drag of a 45 Degree Swept Wing with an NACA 64A006 Section and with a Thickened Leading-edge Section written by George H. Holdaway and published by . This book was released on 1957 with total page 97 pages. Available in PDF, EPUB and Kindle. Book excerpt: This wind-tunnel investigation was conducted at Reynolds numbers of about 7,000,000 based on the mean aerodynamic chord of the wing and the tests covered a Mach number range from 0.6 to 1.2. Two airfoils of the same maximum thickness were tested to evaluate the effect of a large leading-edge radius with increased thickness over the forward 40 percent of the chord on the reliability of the predictions of the supersonic area rule. The basic wing had an aspect ratio of 3, a leading-edge sweep of 45 degrees, a taper ratio of 0.4, and NACA 64A006 sections perpendicular to a line swept back 39.45 degrees, the quarter-chord line of these sections. The modified wing was similar to the basic wing in plan form; however, the leading-edge radius of the modified airfoil was about five times as great as that of the basic airfoil. Both wings were tested with a fineness-ratio-12.5 Sears-Haack body and with this body indented for the respective wings for design Mach numbers of l.05 and 1.20. The basic-wing model was also tested with the body indented for a design Mach number of 1.00.
Book Synopsis Effects of Sweep and Taper on the Longitudinal Characteristics of an Aspect Ratio 3 Wing-body Combination at Mach Numbers from 0.6 to 1.4 by : Earl D. Knechtel
Download or read book Effects of Sweep and Taper on the Longitudinal Characteristics of an Aspect Ratio 3 Wing-body Combination at Mach Numbers from 0.6 to 1.4 written by Earl D. Knechtel and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to assess the effects of sweep and taper ratio on the longitudinal characteristics of a wing-body combination at Mach numbers from 0.6 to 14 and for a Reynolds number of 1,500,000. The wings were 3 percent thick and of aspect ratio 3. Leading-edge sweep was varied from 19.1 to 53.1 degrees at a constant taper ratio of 0.4, and taper ratio was varied from 0 to 0.5 at a constant sweep angle of 53.1 degrees.
