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Author : Robert S. Osborne
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.3/5 (91 download)
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1953 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Edward C. Polhamus
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.3/5 (91 download)
Download or read book Drag Due to Lift at Mach Numbers Up to 2.0 written by Edward C. Polhamus and published by . This book was released on 1953 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Vernard E. Lockwood
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.:/5 (31 download)
Download or read book Lift and Drag Characteristics at Subsonic Speeds and at a Mach Number of 1.9 of a Lifting Circular Cylinder with a Fineness Ratio of 10 written by Vernard E. Lockwood and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : H. Herbert Jackson
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.:/5 (31 download)
Download or read book Free-flight Measurements of the Zero-lift Drag of Several Wings at Mach Numbers from 1.4 to 3.8 written by H. Herbert Jackson and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 902 pages
Book Rating : 4.3/5 (91 download)
Download or read book NASA Technical Note written by and published by . This book was released on 1971 with total page 902 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 112 pages
Book Rating : 4.F/5 ( download)
Download or read book NASA Technical Paper written by and published by . This book was released on 1988 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William Letko
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Experimental Investigation at a Mach Number of 3.11 of the Lift, Drag, and Pitching-moment Characteristics of Five Blunt Lifting Bodies written by William Letko and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : United States. National Aeronautics and Space Administration
Publisher :
ISBN 13 :
Total Pages : 208 pages
Book Rating : 4.F/5 ( download)
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1959 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 494 pages
Book Rating : 4.3/5 ( download)
Download or read book Index of NASA Technical Publications written by and published by . This book was released on 1959 with total page 494 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : United States. National Aeronautics and Space Administration
Publisher :
ISBN 13 :
Total Pages : 500 pages
Book Rating : 4.3/5 (126 download)
Download or read book Index of NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1959 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Emma Jean Landrum
Publisher :
ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.:/5 (317 download)
Download or read book Effects of a Lower Surface Jet on the Lift-drag Ratio of a 45° Sweptback Wing at a Mach Number of 2.01 written by Emma Jean Landrum and published by . This book was released on 1960 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Edwin J. Saltzman
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (317 download)
Download or read book Preliminary Full-scale Power-off Drag of the X-15 Airplane for Mach Numbers from 0.7 to 3.1 written by Edwin J. Saltzman and published by . This book was released on 1960 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Edward J. Hopkins
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (31 download)
Download or read book Comparison of Full-scale Lift and Drag Characteristics of the X-15 Airplane with Wind-tunnel Results and Theory written by Edward J. Hopkins and published by . This book was released on 1962 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 80 pages
Book Rating : 4.:/5 (317 download)
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.
Author : Robert S. Osborne
Publisher :
ISBN 13 :
Total Pages : 112 pages
Book Rating : 4.:/5 (31 download)
Download or read book Aerodynamic Characteristics of a 0.0667-scale Model of the North American X-15 Research Airplane at Transonic Speeds written by Robert S. Osborne and published by . This book was released on 1959 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Robert S. Osborne
Publisher :
ISBN 13 :
Total Pages : 24 pages
Book Rating : 4.:/5 (317 download)
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 written by Robert S. Osborne and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John D. Morrow
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.3/5 (91 download)
Download or read book Flight Investigation at Mach Numbers from 0.6 to 1.7 to Determine Drag and Base Pressures on a Blunt-trailing-edge Airfoil and Drag of Diamond and Circular-arc Airfoils at Zero Lift written by John D. Morrow and published by . This book was released on 1950 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models having rectangular 6-percent-thick wings are presented for a Mach number range of 0.6 to 1.7. Wings of aspect ratio 2.7 having diamond, circular-arc, and blunt-trailing edge airfoil sections were tested. Pressures were measured on the base of the blunt-trailing-edge airfoil which had a rectangular section with a 40-percent-chord beveled leading edge. Although the blunt-trailing-edge airfoil had high drag throughout the Mach number range investigated, because of high base suction pressures, it is believed that the data presented can be used in the design of more nearly optimum blunt-base airfoils. Of the airfoils tested the circular-arc section had lowest drag at high-subsonic speeds, and the diamond section had lowest drag at supersonic speeds.
