Download or read book Aerodynamic Properties of Slender Wing body Combination at Subsonic Transonic and Supersonic Speeds written by John R. Spreiter and published by . This book was released on 1948 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Properties of Slender Wing body Combinations at Subsonic Transonic and Supersonic Speeds written by John R. Spreiter and published by . This book was released on 1948 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: It is further shown that the aerodynamic characteristics of a moderate-aspect-ratio pointed wing at sonic speed may be predictied in a manner mathematically equivalent to that used in the study of a low-aspect-ratio wing.

Download or read book Aerodynamic Properties of Cruciform wing and Body Combinations at Subsonic Transonic and Supersonic Speeds written by John R. Spreiter and published by . This book was released on 1949 with total page 646 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic forces and moments exerted on pitched and yawed wing-body combinations consisting of a slender body of revolution and a cruciform arrangement of thin wings have been investigated by two theoretical methods. One method, an extension of the slender wing-body theory of NACA TN No. 1662, makes possible the determination of simple closed expressions for the load distribution, of simple closed expressions for the load distribution, the forces, and the moments for slender cruciform-wing and body combinations in which the wings may be dissimilar plan form. The second method treats cruciform-wing and body combinations consisting of a body of revolution and identical wings of arbitrary aspect ratio and plan form. The results are valid at subsonic, transonic, and supersonic speeds.

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Ross B. Robinson and published by . This book was released on 1952 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Lowell E. Hasel and published by . This book was released on 1952 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Effects of Wing Incidence on the Aerodynamic Loading Characteristics of a Sweptback Wing body Combination at Transonic Speeds written by Harold L. Robinson and published by . This book was released on 1954 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Subsonic Transonic and Supersonic Aerodynamic Characteristics of a Modified Arrow wing Transport Airplane Configuration written by and published by . This book was released on 1964 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Supersonic Aerodynamic Characteristics of a Low Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1 86 and a Body of Fineness Ratio 20 written by and published by . This book was released on 1960 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.

Download or read book A Supersonic Area Rule and an Application to the Design of a Wing body Combination with High Lift drag Ratios written by Richard T. Whitcomb and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.

Download or read book Theoretical Damping in Roll and Rolling Effectiveness of Slender Cruciform Wings written by Gaynor J. Adams and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: The coefficients of damping in roll and rolling effectiveness (with differential incidence of the horizontal surfaces) are determined for a slender, equal-span, cruciform wing. It is found that the coefficient of damping in ar roll is 62 percent greater than for a plane slender wing of equal aspect ratio, and that the rolling effectiveness is 53 percent less than for a plane slender wing of equal aspect ratio. The analysis can be used in the estimation of the characteristics of a slender, equal-span, cruciform wing having any specified distribution of normal velocity components on the horizontal and vertical surfaces.

Download or read book An Empirically Derived Basis for Calculating the Area Rate and Distribution of Water drop Impingement on Airfoils written by Antonio Ferri and published by . This book was released on 1952 with total page 346 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical Note written by and published by . This book was released on 1948 with total page 548 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of Bonding Between Metals and Ceramics written by H. J. Hamjian and published by . This book was released on 1949 with total page 696 pages. Available in PDF, EPUB and Kindle. Book excerpt: The experiments conducted with boron carbide and each of four metals showed that nickel, cobalt, and iron formed a bonding zone between the metal and the ceramic and that chromium showed satisfactory physical wetting characteristics on the ceramic.

Download or read book Technical Note National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1954 with total page 1078 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book General Theory of Wave drag Reduction for Combinations Employing Quasi cylindrical Bodies with an Application to Swept wing and Body Combinations written by Jack N. Nielsen and published by . This book was released on 1956 with total page 676 pages. Available in PDF, EPUB and Kindle. Book excerpt: The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.

Download or read book Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1952 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1948 with total page 664 pages. Available in PDF, EPUB and Kindle. Book excerpt: