Engineering topics

Praharaj, S. C.

Publications and source records attributed to Praharaj, S. C..

10 records

NASA NTRS1992

Variable gamma computations for a forward-firing Space Shuttle Main Engine

A procedure for solving an axisymmetric SSME nozzle exhausting with an equivalent mass flow of two nozzles is presented for the return-to-launch-site (RTLS) maneuver for an engine-out case. The algorithm incorporates a two-species variable gamma formulation along with diffusion terms associated with a species conservation equation. Coupling of this algorithm is accomplished explicitly to the Navier-Stokes PARC2DR and PARC3DR codes. Axisymmetric results indicate a very complicated flowfield with a bow shock extending to approximately 570 radii in front of the nozzle, and low temperatures on what would be an external tank (ET) aft of the nozzle.

Saladino, A. J.↗

NASA NTRS1989

Further Improvements to Nozzle Boundary Layer Calculations in BLIMPJ

Further improvements made to advance the current Boundary Layer Integral Matrix Procedure - Version J (BLIMPJ) containing previously modeled simplified calculation methods by accounting for condensed phase, thick boundary layer and free stream turbulence effects are discussed. The condensed phase effects were included through species composition effect considered via input to the code and through particle damping effect considered via a turbulence model. The thrust loss calculation procedure for thick boundary layer effects was improved and the optimization of net thrust with respect to nozzle length was performed. The effects of free stream turbulence were approximately modeled in the turbulence model.

Praharaj, S. C.↗

NASA NTRS1987

Boundary layer simulator (BLIMPJ) improvement

Improvements were made to advance the current Boundary Layer Integral Matrix Procedure - Version J (BLIMPJ) containing previously modeled simplified calculation methods accounting for surface roughness, relaminarization, and thick boundary layer effects. These improvements have potential applications in the design of the future Orbit Transfer Vehicles (OTV) engines. The coded wall roughness module was validated successfully against measured data from the LeRC 60-15 degree half-angle conical nozzle. The relaminarization model was modified to include wall cooling and roughness based on a set of test data from the same nozzle. The model was compared against typical data sets for validation in different flow regimes. The thrust loss calculation for thick boundary layer effects was computerized where the iterations between TDK and BLIMPJ proceeded automatically until convergence was achieved. An example is given for a typical OTV nozzle with an area ratio 1293.

Praharaj, S. C.↗

NASA NTRS1984

Boundary layer simulator improvement

High chamber pressure expander cycles proposed for orbit transfer vehicles depend primarily on the heat energy transmitted from the combustion products through the thrust wall chamber wall. The heat transfer to the nozzle wall is affected by such variables as wall roughness, relamarization, and the presence of particles in the flow. Motor performance loss for these nozzles with thick boundary layers is inaccurate using the existing procedure coded BLIMPJ. Modifications and innovations to the code are examined. Updated routines are listed.

Praharaj, S. C.↗

NASA NTRS1984

Orbital flight test Shuttle External Tank flowfield and aerothermal analysis

This paper discusses the evaluation of aerothermal flight measurements made on the orbital flight test Space Shuttle External Tanks (ET). These ETs were instrumented to measure various quantities during flight including heat transfer, pressure and structural temperature. The flight data were reduced and analyzed against math models established from an extensive wind tunnel data base and empirical heat-transfer relationships. This analysis has supported the validity of the current aeroheating methodology and existing data base, but has also identified some problem areas which require methodology modifications.

Praharaj, S. C.↗

NASA NTRS1983

MINIVER upgrade for the AVID system. Volume 1: LANMIN user's manual

The successful design of thermal protection systems for vehicles operating in atmosphere and near space environments requires accurate analyses of heating rate and temperature histories encountered along a trajectory. For preliminary design calculations, however, the requirement for accuracy must be tempered by the need for speed and versatility in computational tools used to determine thermal environments and structural thermal response. The MINIVER program has been found to provide the proper balance between versatility, speed and accuracy for an aerothermal prediction tool. The advancement in computer aided design concepts at Langley Research Center (LaRC) in the past few years has made it desirable to incorporate the MINIVER program into the LaRC Advanced Vehicle Integrated Design, AVID, system. In order to effectively incorporate MINIVER into the AVID system, several changes to MINIVER were made. The thermal conduction options in MINIVER were removed and a new Explicit Interactive Thermal Structures (EXITS) code was developed. Many upgrades to the MINIVER code were made and a new Langley version of MINIVER called LANMIN was created. The theoretical methods and subroutine functions used in LANMIN are described.

Engel, C. D.↗

NASA NTRS1982

Initial Shuttle external tank flight evaluation

The objective of this paper is to evaluate aerothermal flight measurements made on the Space Shuttle External Tank (ET) during its initial flights. The ETs have been adequately instrumented to measure various quantities during flight including heat transfer, pressure, and structural temperature. The flight data have been compared with mathematical models based on an extensive wind tunnel data base, realistic flowfields, and empirical heat-transfer relationships. An analysis of the results points out the validity of the current aeroheating methodology and existing data base, and identifies problem areas in the methodology as indicated by the flight data.

Praharaj, S. C.↗

NASA NTRS1979

Undisturbed flowfield and turbulent heat-transfer analysis on the Space Shuttle external tank

The paper analyzes the existing undisturbed flowfield and turbulent heat-transfer data on smooth models of the Space Shuttle external tank and extends the mathematical model for theoretical calculation of heat-transfer rates presented in an earlier paper to include both the external tank barrel and ogive sections at zero and nonzero angles of attack. Experimental data have been obtained from various wind tunnels which simulated the continuum flow regime in the Shuttle flight trajectory. The model data have been compared with theoretical predictions using realistic flowfields and well-known empirical heat-transfer relationships. The results show that the predictions are good to within the experimental uncertainties of the measured data.

Praharaj, S. C.↗

NASA NTRS1978

Undisturbed heat transfer data analysis on the Space Shuttle External Tank Barrel Section

The paper analyzes the existing continuum undisturbed turbulent heat transfer data on smooth models of the Space Shuttle External Tank and develops a mathematical model for theoretical prediction of heat transfer rates on the External Tank Barrel Section. Experimental data have been obtained from various wind tunnels which simulated the continuum flow regime in the Shuttle flight trajectory. The model data have been compared with theoretical predictions using realistic flow fields and well-known empirical heat transfer relationships. The results show that the predictions are good to within the experimental uncertainties of the measured data.

Praharaj, S. C.↗

NASA NTRS1975

Reentry static stability characteristics of a (Model 471) .005479-scale 146-inch solid rocket booster tested in the NASA/MSFC 14 by 14 inch TWT (SA8F)

A force test of a scale model of the Space Shuttle Solid Rocket Booster was conducted in a trisonic wind tunnel. The model was tested with such protuberances as a camera capsule, electrical tunnel, attach rings, aft separation rockets, ET attachment structure, and hold-down struts. The model was also tested with the nozzle at gimbal angles of 0, 2.5, and 5 degrees. The influence of a unique heat shield configuration was also determined. Some photographs of model installations in the tunnel were taken and are included. Schlieren photography was utilized for several angles of attack.

Johnson, J. D.↗