Numerical solution of Space Shuttle Orbiter flowfield including real-gas effects

Prabhu, Dinesh K.; Tannehill, John C.

doi:10.2514/3.25108

Cited by 21 publications

(11 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The reader is encouraged to keep track of the literature in this field. References [203] and [204] are just samples of the literature; the work of Bhutta et al [205] is of particular note.…”

Section: Parabolized Navier -Stokes Solutions To Chemically Reacting mentioning

confidence: 98%

“…8.3, which should be reviewed by the reader before progressing further. In this section, we will briefly treat a PNS application to equilibrium and nonequilibrium chemically reacting flow as carried out in the recent work of Prabhu and coworkers [203] and [204].…”

Section: Parabolized Navier -Stokes Solutions To Chemically Reacting mentioning

confidence: 99%

“…In [203] the PNS equations were used to solve for the complete, viscous laminar flow over the space shuttle, assuming flow in local chemical equilibrium. Results are given for V 1 ¼ 6.74 km/s, altitude ¼ 71.32 km, and an angle of attack of 40 deg.…”

Section: Parabolized Navier -Stokes Solutions To Chemically Reacting mentioning

confidence: 99%

“…17 Mach-number contours from PNS calculations of the viscous flow over the space shuttle where x/L 5 0.4: a) calorically perfect gas with g 5 1.2 and b) equilibrium chemically reacting air (from Prabhu and Tennehill[203]). …”

mentioning

confidence: 99%

See 3 more Smart Citations

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Anderson¹

2006

958

603

View full text Add to dashboard Cite

Data and information appearing in this book are for information purposes only. AIAA is not responsible for any injury or damage resulting from use or reliance, nor does AIAA warrant that use or reliance will be free from privately owned rights. Downloaded by Stanford University on September 30, 2012 | http://arc.aiaa.org | , for all their love and understanding Downloaded by Stanford University on September 30, 2012 | http://arc.aiaa.org |

show abstract

Section: Parabolized Navier -Stokes Solutions To Chemically Reacting mentioning

confidence: 98%

Section: Parabolized Navier -Stokes Solutions To Chemically Reacting mentioning

confidence: 99%

Section: Parabolized Navier -Stokes Solutions To Chemically Reacting mentioning

confidence: 99%

mentioning

confidence: 99%

See 2 more Smart Citations

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Anderson¹

2006

958

603

View full text Add to dashboard Cite

show abstract

“…In Fig. 6(b), tunnel pressure distributions are compared with those obtained in flight and by numerical calculation at a stagnation enthalpy of 24 MJ/kg< 18 ). It can be seen that the low surface pressures immediately aft of the canopy are evident in both the tunnel and the flight data, as well as the calculations.…”

Section: Pressure Data Windward Pressure Datamentioning

confidence: 99%

Experiments on Space Shuttle Orbiter models in a free piston shock tunnel

Krek

Stalker

1992

Aeronaut. j.

View full text Add to dashboard Cite

Heat transfer and pressure measurements were made on a model of the United States Space Shuttle Orbiter in the University of Queensland's T4 shock tunnel at three angles of attack, with stagnation enthalpies which varied by a factor of 11, from 2·1 MJ/kg to 23 MJ/kg and normal shock Reynolds numbers which varied by a factor of 38, from 2·1 x l04 to 8·l x 105. Leeward pressure results were obtained for comparison with flight data and equilibrium calculations, but the majority of the experiments were conducted to investigate the heat transfer distributions around the shuttle model. Both the windward and leeward heat transfer results exhibit the onset of transition to turbulent flow. The leeward results are compared with flight data as well as with conventional wind tunnel data, and are used to establish trends associated with variation in the major flow and geometry parameters. It was found that although high enthalpy effects could be important, Reynolds number effects played a dominant role in determining the flow.

show abstract

High-temperature effects in hypersonic flows

Prabhu

1995

Sadhana

View full text Add to dashboard Cite

The hypersonic (M = 25) flow past a 10 ° right circular cone at 0 ° angle of attack has been computed using an implicit, noniterative, finitedifference scheme for the Parabolized Navier-Stokes (PNS) equations. Three different gas models have been considered in the study-(1) ideal gas (y = constant), (2) equilibrium air, and (3) five species (N 2, 0 2, NO, N, O) chemical nonequilibrium air. For the nonequilibrium air case, three different models have been considered-(a) one in which the constituent species have no internal structure (i.e., species are ideal gases), (b) one in which the constituent species have internal structure (i.e., species are thermally perfect gases), and (c) one in which the species have internal structure and their thermodynamic properties have been obtained from quantum mechanical and spectroscopic calculations.

show abstract

Numerical solution of Space Shuttle Orbiter flowfield including real-gas effects

Cited by 21 publications

References 23 publications

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Hypersonic and High-Temperature Gas Dynamics, Second Edition

Experiments on Space Shuttle Orbiter models in a free piston shock tunnel

High-temperature effects in hypersonic flows

Contact Info

Product

Resources

About