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Book Scientific and Technical Aerospace Reports

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1963 with total page 1042 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Technical Abstract Bulletin

Download or read book Technical Abstract Bulletin written by and published by . This book was released on 1981 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Transonic Wind Tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Five Nose Cones Designed for Supersonic Impact

Download or read book Transonic Wind Tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Five Nose Cones Designed for Supersonic Impact written by John P. Jr Mugler and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind tunnel Investigation at Mach Numbers from 1 47 to 4 62 of Static Aerodynamic Characteristics of Twelve Nose Cones Designed for Supersonic Impact

Download or read book Wind tunnel Investigation at Mach Numbers from 1 47 to 4 62 of Static Aerodynamic Characteristics of Twelve Nose Cones Designed for Supersonic Impact written by and published by . This book was released on 1961 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Wind Tunnel Tests of Rectangular Finned Variable Gap Tangent Ogive cylinder Model at Mach Numbers 1 75 to 4 50

Download or read book Wind Tunnel Tests of Rectangular Finned Variable Gap Tangent Ogive cylinder Model at Mach Numbers 1 75 to 4 50 written by Neil Arthur Zarin and published by . This book was released on 1964 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Blockage Study of a 1 16 scale B 1 Inlet Model in the 1 ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility

Download or read book Blockage Study of a 1 16 scale B 1 Inlet Model in the 1 ft Transonic and Supersonic Tunnels of the Propulsion Wind Tunnel Facility written by C. F. Anderson and published by . This book was released on 1972 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 1-ft Aerodynamic Wind Tunnels (1T and 1S) of the Propulsion Wind Tunnel Facility to obtain estimates of the performance available for the full-scale B-1 inlet/engine tests in the 16-ft Propulsion Wind Tunnels (16T and 16S). Data were obtained with two nacelle configurations and four wing configurations. The maximum test section blockage was 17 percent. Data were obtained at Mach numbers from 0.55 to 1.30 and from 1.71 to 2.30. The tunnel performance for each configuration was evaluated relative to the others and with regard to the capabilities of the 16-ft tunnels. The results of these tests indicate that the available tunnel performance is significantly compromised with the nacelle configuration which has been selected for the full-scale test. The maximum Mach number estimated to be available for the full-scale test in Tunnel 16T is 1.0. To obtain a full range of engine operating points, however, testing should be restricted to M

Book Wind Tunnel Tests of a 5 Scale Semi conical A3J 1 Inlet Model at Mach Numbers of 0 9 1 2 1 4 1 6 1 8 and 2 05

Download or read book Wind Tunnel Tests of a 5 Scale Semi conical A3J 1 Inlet Model at Mach Numbers of 0 9 1 2 1 4 1 6 1 8 and 2 05 written by Marion R. Bottorff and published by . This book was released on 1957 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1 5 to 19 5

Download or read book An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1 5 to 19 5 written by C. J. Schueler and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the test section flow blockage characteristics was conducted in the 12- by 12 inch supersonic wind tunnel (Tunnel E-1) of the Von Karman Gas Dynamics Facility (AEDC). The purpose of the tests was to determine whether a method of predicting the maximum size model which will permit the establishment of supersonic flow, based on the model frontal area and bow shock-wave strength, is applicable over a wide range of Mach numbers. The tests conducted over the Mach number range from 1.5 to 5 using test models consisting of 15, 20, and 20 degrees half-angle cones, cone-cylinder combinations, and a series of discs. The inadequacy of the one dimensional, normal shock theory for predicting allowable model sizes was reconfirmed in these tests. Furthermore a correlation based on shock wave strength and model frontal area was found to be suitable only over a limited range of Mach numbers. Permissible hemisphere-cylinder model sizes from several wind tunnels covering the Mach number range from 1.5 to 19.5 are also presented.

Book Evaluation of Critical Sting Length on a 7 deg Cone as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0 2 Through 1 3

Download or read book Evaluation of Critical Sting Length on a 7 deg Cone as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0 2 Through 1 3 written by and published by . This book was released on 1981 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were conducted to provide sting-support interference information for planning and directing wind tunnel tests at subsonic and transonic Mach numbers. Sting-length effects on dynamic stability derivatives, static pitching moment, and base pressure of a blunt, flat-base 7- deg cone were investigated at Mach numbers 0.2 to 1.3 in the Arnold Engineering Development Center (AEDC) Propulsion Wind Tunnel Facility (PWT). Two frequencies of oscillation, nominally 5.3 and 2.9 Hz, were investigated. The boundary-layer state at the model base was turbulent for all Mach numbers greater than 0.2. The interference effects of two types of model-wake splitter plates were also investigated. The results showed that the critical sting length depended on the Mach number, angle of attack, and type of data used as the interference indicator. A critical sting length of three model diameters was determined to be suitable for all test conditions for the ratio of sting-diameter-to-model-base- diameter (0.22) for this test.

Book Design for Control of Projectile Flight Characteristics

Download or read book Design for Control of Projectile Flight Characteristics written by United States. Army Materiel Command and published by . This book was released on 1966 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt: