Download or read book An Experimental Investigation at Supersonic Mach Numbers of Base Drag of Various Boattail Shapes with Simulated Base Rocket Exhaust written by Joseph Huerta and published by . This book was released on 1969 with total page 45 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the effect of boattail geometry and simulated base rocket nozzle flow on overall base drag. All tests were performed at Mach numbers 2.50, 3.00 and 3.50. Reasonable prediction of base drag for the reported boattail shapes can be made by using approximate and empirical equations. A conical boattail produced less drag than the other boattail shapes investigated. The maximum nozzle stagnation to free- stream pressure ratio reported is 315. (Author).
Download or read book A Free flight Investigation of the Effects of Simulated Sonic Turbojet Exhaust on the Drag of a Boattail Body with Various Jet Sizes from Mach Number 0 87 to 1 50 written by Ralph A. Falanga and published by . This book was released on 1955 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three 7.5 degree boattail bodies of revolution with varying base-annulus areas and jet sizes provided with simulated-turbojet-exhaust rocket motors were flight-tested to determine the jet interference effects on drag over a Mach number range from approximately 0.87 to 1.5. The results indicated that in the transonic and low-supersonic speed range the jet caused positive pressure increments on the base and boattail which appreciably reduced the configuration drag from the power-off condition. At the high supersonic speeds, the jet caused positive pressure increments only on the base and resulted in a smaller reduction in body drag from power-off conditions.
Download or read book Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total Base and Skin friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag written by August F. Bromm and published by . This book was released on 1953 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effect of Boattailing on the Drag Coefficient of Cone cylinder Projectiles at Supersonic Velocities written by Elizabeth R. Dickinson and published by . This book was released on 1954 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1967 with total page 866 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Notices of Changes in Classification Distribution and Availability written by and published by . This book was released on 1999 with total page 490 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total Base and Skin friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag written by August F. Bromm 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 conducted in the Langley 9-inch supersonic tunnel to determine the effect of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag at zero lift of seven boattail bodies of revolution designed for minimum wave drag according to NACA Technical Note 2550. The investigation covered a Reynolds number range from approximately 1,000,000 to 10,000,000 at Mach numbers of 1.62, 1.93, and 2.41, respectively. The results show that base drag and, in general, the total drag increase with increasing values of the ratio of base area to maximum area B/S(max), although the results reported in NACA Technical Note 3054 showed that the wave drag decreased with ticreasing values of B/S(max). The laminar skin-friction drag is in agreement with the theoretical predictions used, and, within the Mach number range of these tests, the simple Blasius incompressible theory gives a satisfactory prediction. Except for values of B/S(max) near 1, the Reynolds number of transition increases with increasing Mach number and, as this ratio approaches 1, this variation is seen to reverse. These variations in Reynolds number of transition with Mach number appear to be associated with the changes in pressure gradient over the rear of the bodies.
Download or read book Experimental Investigation of the Effects of Viscosity on the Drag of Bodies of Revolution at a Mach Number of 1 5 written by Dean R. Chapman and published by . This book was released on 1947 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Tests were conducted to determine the effects of viscosity on the drag and base pressure characteristics of various bodies of revolution at a Mach number of 1.5. The models were tested both with smooth surfaces and with roughness added to evaluate the effects of Reynolds number for both laminar and turbulent boundary layers. The principal geometric variables investigated were after-body shape and length-diameter ratio. For most models, force tests and base pressure measurements were made over a range of Reynolds numbers, based on model length, from 0.6 million to 5.0 millions. Schlieren photographs were used to analyze the effects of viscosity on flow separation and shock-wave configuration near the base and to verify the condition of the boundary layer as deduced from force tests. The results are discussed and compared with theoretical calculations.
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1959 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of the Effects of Support Interference on the Drag of Bodies of Revolution at a Mach Number of 1 5 written by Edward W. Perkins and published by . This book was released on 1951 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains the results of an experimental investigation to determine the effects of support interference on the base drag and fore drage of two bodies of revolution. The results show that the rear supports affect the drag of a body of revolution through the immediate influence on the pressures acting over the rear portions of the body and thus the magnitude of the interference depends on the afterbody shape of the model, the Reynolds number of flow, and the condition of the boundary layer.
Download or read book Free flight Investigation at Transonic Speeds of Drag Coefficients of a Boattail Body of Revolution with a Simulated Turbojet Exhaust Issuing at the Base from Conical Short length Ejectors written by Ralph A. Falanga and published by . This book was released on 1956 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Four 7.5 degree boattail bodies of revolution with secondary air scoops were tested in free-flight to find the change in drag-coefficient when a simulated turbojet exhaust issued from conical short-length ejectors. Models 1 and 2 each had single scoops and a spacing ratio of 0.387, whereas model 3 had two scoops and the same spacing ratio as models 1 and 2. Model 4 had a single scoop and a spacing ratio of 0.097. All models tested had the same diameter ratio of 1.256. The results indicated that the jet-on total drag coefficients were lower throughout the test Mach number range than corresponding jet-off values of the forebody drag coefficient. Furthermore, it appeared that increasing the corrected weight-flow ratio by doubling the number of secondary scoops increased the increment between jet-on and jet-off drag coefficients.
Download or read book NASA Reference Publication written by and published by . This book was released on 1977 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1957 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1982 with total page 1282 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Download or read book A Base Drag Reduction Experiment on the X 33 Linear Aerospike SR 71 Experiment LASRE Flight Program written by Stephen A. Whitmore and published by . This book was released on 1999 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Drag reduction tests were conducted on the LASRE/X-33 flight experiment. The LASRE experiment is a flight test of a roughly 20-percent scale model of an X-33 forebody with a single aerospike engine at the rear. The experiment apparatus is mounted on top of an SR-71 aircraft. This paper suggests a method for reducing base drag by adding surface roughness along the forebody. Calculations show a potential for base drag reductions of 8 to 14 percent. Flight results corroborate the base drag reduction, with actual reductions of 15 percent in the high-subsonic flight regime. An unexpected result of this experiment is that drag benefits were shown to persist well into the supersonic flight regime. Flight results show no overall net drag reduction. Applied surface roughness causes forebody pressures to rise and offset base drag reductions. Apparently the grit displaced streamlines outward, causing forebody compression. Results of the LASRE drag experiments are inconclusive and more work is needed. Clearly, however, the forebody grit application works as a viable drag reduction tool.
Download or read book Investigation of the Drag of Blunt nosed Bodies of Revolution in Free Flight at Mach Numbers from 0 6 to 2 3 written by Harvey A. Wallskog and published by . This book was released on 1953 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation at Mach Numbers of 0 20 to 3 50 of Blended Wing body Combinations of Sonic Design with Diamond Delta and Arrow Plan Forms written by George H. Holdaway and published by . This book was released on 1960 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
