Download or read book Force and Pressure recovery Characteristics at Supersonic Speeds of a Conical Nose Inlet with Bypass Discharging Outward from the Body Axis written by Andrew Beke 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 Research Memorandum written by and published by . This book was released on 1953 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Force and Pressure Recovery Characteristics at Supersonic Speeds of a Conical Spike Inlet with Bypasses Discharging in an Axial Direction written by J.L. Allen and published by . This book was released on 1953 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Force and Pressure Recovery Characteristics at Supersonic Speeds of a Conical Spike Inlet with a Bypass Discharging from the Top Or Bottom of the Diffuser in an Axial Direction written by J.L. Allen and published by . This book was released on 1953 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Research Abstracts and Reclassification Notice written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1956 with total page 716 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Force and Pressure recovery Characteristics of a Conical type Nose Inlet Operating at Mach Numbers of 1 6 to 2 0 and at Angles of Attack to 9 Degrees written by Andrew Beke and published by . This book was released on 1952 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Some Internal flow Characteristics at Zero Flight Speed of an Annular Supersonic Inlet and an Open nose Inlet with Sharp and Rounded Lips written by Joseph R. Milillo and published by . This book was released on 1954 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static tests of an annular conical-shock inlet and an open-nose conical inlet with three lip shapes were conducted at the Langley 8-foot transonic tunnel. Measurements of pressure recovery, surface pressure, and total pressure were made through a mass-flow range extending to choking. The results indicate that the two inlets with thin sharp lips had about the same relatively poor pressure-recovery characteristics and choked at a mass-flow rate of about 78 percent of the theoretical maximum. However, both the pressure recovery and choking mass-flow rate were greatly improved by replacing the sharp lip by two alternate shapes with lip roundness and internal contraction just behind the inlet lip.

Download or read book Effect of Yaw and Angle of Attack on Pressure Recovery and Mass flow Characteristics of a Rectangular Supersonic Scoop Inlet at a Mach Number of 2 71 written by Raymond J. Comenzo and published by . This book was released on 1954 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Preliminary Attempts at Isothermal Compression of a Supersonic Air Stream written by E. Perchonok and published by . This book was released on 1956 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Guided by analytical predictions, preliminary experiments were undertaken in an attempt to achieve isothermal (constant static temperature) compression of a supersonic air stream. Application of the process to a supersonic inlet diffuser at free-stream Mach numbers of 1.9 and 3.0 did not produce the theoretically predicted total-pressure rise. Large total-pressure losses due to momentum exchange between the inlet air stream and the coolant occurred, as expected, but the compensating rise in pressure theoretically associated with the available evaporation cooling was not observed. Tests at a Mach number of 3.0 with a heated air stream and multipoint upstream injection suggest that some gain in diffuser pressure recovery might be obtained with a full-scale inlet at the high stagnation temperature of supersonic flight.

Download or read book Dynamics of a Supersonic Inlet with Adjustable Bypass in Combination with a J34 Turbojet Engine written by Fred Allen Wilcox and published by . This book was released on 1956 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Estimation of Shock Pressure Recovery and External Drag of Conical Centre body Intakes at Supersonic Speeds written by Aeronautical Research Council (Great Britain) and published by . This book was released on 1959 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Estimation of Shock Pressure Recovery and External Drag of Conical Centre body Intakes at Supersonic Speeds written by E. L. Goldsmith and published by . This book was released on 1953 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer written by Wallace F. Davis and published by . This book was released on 1948 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A model having a nozzle upstream of an annular duct inlet for the purpose of ejecting high-velocity air into the boundary layer of the flow along the forebody was tested at Mach numbers between 1.36 and 2.01. The size and location of the nozzle and the total pressure of the air in the jet were varied to determine their effects upon the pressure recovery attainable after diffusion through the duct inlet. The results of the tests showed that the maximum total-pressure recovery was greater than that of a model having no air ejected. The causes of the greater recovery were the delay in the separation of the boundary layer that resulted from mixing between the boundary layer and the jet and also the reduction in the intake Mach number caused by an oblique shock wave that originated from the nozzle outlet when the free boundary of the jet was divergent.

Download or read book The estimation of shock pressure recovery and external drag of conical centre body intakes at supersonic speeds written by E. L. Goldsmith and published by . This book was released on 1959 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: Methods for estimating drag and pressure recovery under conditions of reduced mass flow are presented, and the results compared with experimental values.

Download or read book Numerical Study of Control of Dynamic Properties of a Supersonic Inlet Using Bypass Bleed written by Clarence W. Matthews and published by . This book was released on 1971 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer written by George B. Brajnikoff and published by . This book was released on 1948 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report contains the results of an experimental investigation made at Mach numbers between 1.36 and 2.01 of the total-pressure recovery attainable with a model having a ramp ahead of an annular inlet for the purpose of reducing the entrance Mach number by means of an oblique shock wave. It was found that the recovery improved considerably with increasing ramp angle and that a model with a 15 degree ramp produced approximately four-fifths of the recovery through a normal shock wave occurring at the free-stream Mach number. Use of ramp angles greater than 15 degrees resulted in unsteady flow through the induction system and a reduction in recovery.

Download or read book Effect of Nose Bluntness on Aerodynamic Characteristics of Flared Body at Supersonic Speed written by Takashi Tani and published by . This book was released on 1969 with total page 7 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of nose bluntness on the drag force for the conical flare in supersonic flow is treated. The approximate calculation reported at 6th ISTS by one of the present authors is modified for the flowfield around the cylindrical body with blunt nose. Using the correection based on the loss of the total pressure through the strong shock wave, our estimation gives fairly good agreement with the experimental value. Experimental and analytical treatments for rotational flowfield are also conducted.