Three-Dimensional Nozzle Design for Maximum Thrust. Volume I. Theoretical Development and Results

Item

Title
Three-Dimensional Nozzle Design for Maximum Thrust. Volume I. Theoretical Development and Results
Date
1970
Index Abstract
Not Available
Photo Quality
Not Needed
Report Number
AFAPL TR 70-79 Volume 1
Creator
Snyder, Lynn E,
Thompson, H. Doyle
Corporate Author
Purdue University Jet Propulsion Center
Laboratory
Air Force Aero Propulsion Laboratory
Date Issued
1970-10-28
Extent
180
NTRL Accession Number
AD878642
Identifier
AD0878642
Access Rights
Export Control
Distribution Classification
1
Contract
F33615-67-C-1068
DoD Project
None Given
DoD Task
None Given
DTIC Record Exists
No
Distribution Change Authority Correspondence
AFAPL LTR
Distribution Conflict
No
Abstract
The problem of designing three-dimensional (nonaxisymmetric) supersonic nozzles which produce the maximum axial thrust for a prescribed upstream flow field, mass flow rate, exit lip shape and position, and ambient pressure was formulated and numerically solved. The formulation was written to consider a three-dimensional, supersonic, isoenergetic, homentropic flow of a perfect gas. The axial thrust and mass flow rate were written as integrals over a control surface which was constrained to pass through the exit lip of the nozzle. The functional to be maximized was formed by summing the integral equation for the axial thrust and the integral equation for the mass flow rate times a Lagrange multiplier. The fixed length and fixed ambient pressure constraints were imposed by substitution into the variational problem. The numerical solution technique was programmed for the CDC 6500 computer. The results confirm that the three-dimensional optimal nozzles designed using this technique are significantly better than three-dimensional nozzles that have identical initial conditions and have comparable overall dimensions. Furthermore, the results show that two-dimensional or axisymmetric methods are not adequate for designing three-dimensional optimum nozzles.
Report Availability
Full text available
Publisher
Wright-Patterson Air Force Base, OH : Air Force Aero Propulsion Laboratory, Air Force Systems Command
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
AFAPLTR70-079volume01.pdf