Download or read book Pressure Measurements on Sharp and Blunt 5 Degreee and 15 Degree half angle Cones at Mach Number 3 86 and Angles of Attack to 100 Degrees written by James L. Amick and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Measurements on Sharp and Blunt 5 Degreee and 15 Degree half angle Cones at Mach Number 3 86 and Angles of Attack to 100 Degrees written by James L. Amick and published by . This book was released on 1961 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Measurements on Sharp and Blunt 5 and 15 half angle Cones at Mach Number 3 86 and Angles of Attack to 100 written by James L. Amick and published by . This book was released on 1961 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Laminar Heat transfer and Pressure Measurements at a Mach Number of 6 on Sharp and Blunt 15 Degree Half angle Cones at Angles of Attack Up to 90 Degrees written by RAUL J. CONTI and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer and pressure distributions were measured on sharp and blunt 15 degree half-angle cones. The flow was near conical on the windward side of the models up to an angle of attack of about 60 degrees. At angles of attack above 70 degrees the flow departed noticeably from conical characteristics. Heat-transfer and pressure measurements were found to agree satisfactorily with theories of simple application. At large angles of attack the effects of nose bluntness are very small in the region beyond two nose radii from the point of tangency. (Author).
Download or read book Laminar Heat transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15 Half angle Cones at Angles of Attack Up to 90 written by Raul Jorge Conti and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
Download or read book Laminar Heat transfer and Pressure Measurement at a Mach Number of 6 on Sharp and Blunt 15 Half angle Cones at Angles of Attack Up to 90 written by Raul J. Conti and published by . This book was released on 1961 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Static Force Tests at Mach 8 of Sharp and Blunt 20 deg Half angle Cones with a Blunt 70 deg Swept Delta Wing written by G. H. Merz and published by . This book was released on 1962 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Static Pressure on Sharp and Blunt Cones in Conical and Parallel Low density Flow written by Max Kinslow and published by . This book was released on 1974 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The static pressure distribution on sharp and blunt 10-deg half-angle cones was measured under rarefied conditions in both a uniform and a source flow field. Angle of attack of the cones was varied up to 10 deg. Pressure distributions are presented for cold-wall conditions at 18.0 = or
Download or read book Base Pressure Measurements on Sharp and Blunt 9 Cones at Mach Numbers from 3 50 to 9 20 written by Neil Arthur Zarin and published by . This book was released on 1965 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Measurements of Pressure and Local Heat Transfer on a 20 Cone at Angles of Attack Up to 20 for a Mach Number of 4 95 written by Jerome D. Julius and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free flight Measurement of Drag and Static Stability for a Blunt nosed 10 Half angle Cone at Mach Number 15 written by Dale L. Compton and published by . This book was released on 1961 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Base Pressure Measurements on Sharp and Blunt 9 Degree Cones at Mach Numbers from 3 50 to 9 20 written by Neil A. Zarin and published by . This book was released on 1965 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Base pressure measurements were made on sharp and hemispherically blunted 9 degree cones at Mach numbers from 3.50 to 9.20. The data obtained are compared to experimental data and to data from semiempirical analyses from other sources. An empirical correlation for the base pressure data is presented. The relative contributions of base and form drag to total drag are compared. (Author).
Download or read book Static Aerodynamic Characteristics of Short Blunt Cones with Various Nose and Base Cone Angles at Mach Numbers from 0 6 to 5 5 and Angles of Attack to 180 Degrees written by Stuart L. Treon and published by . This book was released on 1961 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Compilation of Longitudinal Aerodynamic Characteristics Including Pressure Information for Sharp and Blunt nose Cones Having Flat and Modified Bases written by Sandia Corporation and published by . This book was released on 1965 with total page 596 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Measured and Predicted Shock Shapes and Aerodynamic Coefficients for Blunted Cones at Incidence in Helium at Mach 20 3 written by Robert L. Calloway and published by . This book was released on 1979 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental values of shock shapes (alpha = 0 degrees and 10 degrees) and static aerodynamic coefficients (alpha = -4 degrees to 12 degrees) for sharp and spherically blunted cones having cone half-angles of 30, 45, 60, and 70 degrees and nose bluntness ratios of 0, 0.25, and 0.50 are presented. Shock shapes were also measured at 0 degree angle of attack by using a flat-faced cylinder (90 degree cone) and a hemispherically blunted cylinder (sphere). All tests were conducted in helium (gamma = 5/3) at a free-stream Mach number of 20.3 and a unit free-stream Reynolds number of 22,400,000 per meter. Comparisons between measured values and predicted values were made by using several numerical and simple engineering methods.
Download or read book Pressure Distribution on a 5 6 Degree Blunt Cone at Mach 14 written by Eric G. Friberg and published by . This book was released on 1968 with total page 77 pages. Available in PDF, EPUB and Kindle. Book excerpt: The pressure distribution around a 5.6 deg half-angle cone with various nose bluntness ratios was measured in a 20-inch hypersonic wind tunnel at Mach 14 and Re 160,000. An empirical expression for the circumferential pressure distribution at small angles of attack is derived which allows the integration of normal pressure components in closed form. Correlation of the pressure data along the most windward ray at angle of attack by means of the tangent cone concept is shown to be possible if viscous interaction is negligible. For the most windward ray of the 5.6 deg cone this is the case for positive angles of attack only. At negative angles of attack the viscous effects dominate and prevent the correlation. The pitching moment derivative was calculated for several noses on the basis of the measured pressure distributions at angles of attack. (Author).
Download or read book Handbook of Inviscid Sphere cone Flow Fields and Pressure Distributions written by Alfred Merle Morrison and published by . This book was released on 1975 with total page 576 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains numerical tables of aerodynamic coefficients and surface pressure distributions for sphere cone configurations as a function of angle of attack and Mach number. These results were generated by an NSWC/WOL computer code based on a finite difference solution of the steady inviscide three-dimensional compressible flow equation for a perfect gas [upsilon]= 1.4. Cone half angles of 50, 60, 80, 90, 100, 150 and 200 are considered. Truncated values are obtained at axial stations to a length of 200 times the sphere radius, over a Mach number range of 3.5, 5, 10, 20, 25 and 30, for an angle-of-attack span of 10, 30, 50, and 100. Center-of-pressure location, and axial- and normal-force coefficients are tabularly presented at each axial-length increment station. Surface pressure distributions are also presented at each axial-length increment station, including seven meridian plane angles over the half plane from windward to leeward ray. The techniques utilized in generating the tables are described, and comparisons between computed values and values measured in some wind-tunnel experiments are presented. The presentation format is discussed to establish the mechanics necessary to use the tables. The tables are divided into two volumes; the first containing pressure information, and the second, aerodynamic information.
