Download or read book The Zero lift Drag of a 60 degrees Delta wing body Combination AGARD Model 2 Obtained from Free flight Tests Between Mach Numbers of 0 8 and 1 7 written by Robert O. Piland and published by . This book was released on 1954 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Zero lift Drag of a 60 Degree Delta wing body Combination AGARD Model 2 Obtained from Free flight Tests Between Mach Numbers of 0 8 and 1 7 written by Robert O. Piland and published by . This book was released on 1954 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: The zero-lift drag of a 60 degree delta-wing-body combination (designated AGARD Model 2) has been determined by free-flight tests of two models between Mach numbers of 0.8 and 1.7. These Mach numbers correspond to Reynolds numbers, based on body length, of 4,000,000 and 12,000,000, respectively. An estimate of the drag of the configuration was made by summing the estimates of the drag of the various components. The agreement between measured and estimated drag is good.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1966 with total page 1492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Large scale Flight Measurements of Zero lift Drag and Low lift Drag of 10 Wing body Configurations at Mach Numbers from 0 8 to 1 6 written by John D. Morrow and published by . This book was released on 1953 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Results of Flight Tests to Determine the Zero lift Drag Characteristics of a 60 Degree Delta Wing with NACA 65 006 Airfoil Section and Various Double wedge Sections at Mach Numbers from 0 7 to 1 6 written by Clement J. Welsh and published by . This book was released on 1950 with total page 15 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 equipped with 60 degree swept-back delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.
Download or read book Results of Flight Tests to Determine the Zero lift Drag Characteristics of a 60 Degrees Delta Wing with NACA 65 006 Airfoil Section and Various Double wedge Sections at Mach Numbers from 0 7 to 1 6 written by Clement J. Welsh and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effect of Inlet Installation on the Zero lift Drag of a 60 Degree Delta wing body Configuration from Flight Tests at Mach Numbers from 0 8 to 1 86 written by Charles F. Merlet and published by . This book was released on 1955 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of a Flight Investigation to Determine the Zero Lift Drag Characteristics of a 60 Deg Delta Wing with NACA 65 006 Airfoil Section and Various Double Wedge Sections at Mach Numbers from 0 7 1 6 written by and published by . This book was released on 1956 with total page 16 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 equipped with 60 deg sweptback delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness. The results of the investigation showed that, of the double-wedge sections with 6 percent thickness, the two sections with positions of maximum thickness at 20 and 50 percent of the chord had drag coefficients approximately equal through the transonic and supersonic Mach number range and had similarly occurring drag rises. The section with position of maximum thickness at 80 percent chord had a drag rise occurring at a Mach number M of approximately 0.15 lower than the drag rise of the other two sections. At M = 1.0, this section had drag coefficients more than twice as large as those of the other two sections; however, this difference decreased with increasing supersonic Mach numbers. The wing drag calculated by the linearized theory was in qualitative agreement with the test results in indicating the effects of varying the position of maximum thickness. The double-wedge section of 5 percent thickness with position of maximum thickness at 50 percent chord had fairly constant drag coefficients throughout the supersonic region, which ranged from about 50 to 80 percent of the drag coefficients for the similar section with twice the thickness ratio. The theoretical wing drag for this section was in very good agreement with the experimental value. The NACA 65-006 airfoil section had lower drag coefficients throughout the test region than any of the double-wedge sections of the same thickness ratio, although at the highest Mach numbers covered by these tests, the differences became very small.
Download or read book Results of a Flight Investigation to Determine the Zero lift Drag Characteristics of a 60 Degree Delta Wing with NACA 65 006 Airfoil Section and Various Double wedge Sections at Mach Numbers from 0 7 to 1 6 written by Clement J. Welsh and published by . This book was released on 1956 with total page 13 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 equipped with 60 deg sweptback delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.
Download or read book Flight Stability and Automatic Control written by Robert C. Nelson and published by WCB/McGraw-Hill. This book was released on 1998 with total page 441 pages. Available in PDF, EPUB and Kindle. Book excerpt: The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.
Download or read book Measured and Predicted Section Wave Drag Coefficients at a Mach Number of 1 6 for a Delta Wing with Two Airfoil Sections written by Frederick C. Grant and published by . This book was released on 1959 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free flight Investigation to Obtain Drag at lift and Stability Data for a 60 Degree Delta wing body Configuration Over a Mach Number Range of 1 3 to 1 6 written by Clement J. Welsh and published by . This book was released on 1955 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flight tests have been made of a rocket-propelled 60 degree delta-wing-body configuration; the wing airfoil section was NACA 0003-63. Drag at lift and stability data were obtained for a Mach number range of 1.28 to 1.6.
Download or read book Journal of the Royal Aeronautical Society written by and published by . This book was released on 1961 with total page 986 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Some Section Modifications and Protuberances on the Zero lift Drag of Delta Wings at Transonic and Supersonic Speeds written by Carl A. Sandahl and published by . This book was released on 1954 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effect of Inlet Installation of the Zero lift Drag of a 60 Delta wing body Configuration from Flight Tests at Mach Numbers from 0 8 to 1 86 written by Charles F. Merlet and published by . This book was released on 1958 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
