Flight boundary layer transition measurements on a slender cone at Mach 20

Wright, Robert L.; Zoby, E. V.

doi:10.2514/6.1977-719

Cited by 37 publications

(16 citation statements)

References 1 publication

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“…9 In the free-ight test, a 4-m-long, 5-deg half-angle cone was monitored as it entered the atmosphere from 30.48 to 18.29 km around Mach 20. Pressure and temperature measurementswere taken along the surfaceof the cone, allowinglocal ow conditionsto be deduced.…”

Section: Free-flight Re-entry F Testmentioning

confidence: 99%

Enthalpy Effects on Hypervelocity Boundary-Layer Transition: Ground Test and Flight Data

Adam

Hornung

1997

Journal of Spacecraft and Rockets

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Boundary-layer-transitionexperiments on a 5-deg half-angle cone at 0-deg angle of attack were performed in the T5 hypervelocity shock tunnel. The test gases investigated included air, nitrogen, and carbon dioxide. Reservoir enthalpies were varied from 3 to 27 MJ/kg and reservoir pressures from 10 to 95 MPa, depending on the gas and tunnel settings. No clear relationship is found to exist between the transition Reynolds number based on the boundary-layer-edge conditions and the reservoir enthalpy. However, when the reference temperature conditions are used instead, the different test gases are distinguishable and ordered according to their dissociation energy. Data from a free-ight experiment are also compared with the shock tunnel experiments. When the transition Reynolds numbers are evaluated at the boundary-layer-edge conditions, they are an order of magnitude higher than the tunnel results. However, when the reference conditions are used, the ight data fall within the same range as the experiments, although the trend with reservoir enthalpy is reversed. Nomenclatureh = enthalpy, MJ/kg M = Mach number P = pressure, Pa P q = heat transfer rate, MW/m 2 Re = Reynolds number r = recovery factor St = Stanton number T = temperature, K u = velocity, m/s x = axial distance, m ¹ = viscosity, kg/m-s ½ = density, kg/m 3 Subscripts a = adiabatic e = boundary-layer edge tr = transition w = wall 0 = reservoir 1 = freestream Superscript ¤ = reference condition

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Section: Free-flight Re-entry F Testmentioning

confidence: 99%

Enthalpy Effects on Hypervelocity Boundary-Layer Transition: Ground Test and Flight Data

Adam

Hornung

1997

Journal of Spacecraft and Rockets

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“…Reentry F [8] has provided strong motivation and inspiration for the academic study of foundational scientific issues relevant to hypersonic systems and inspired the HIFiRE program to seek the open publication of as much data from the program as current policy will allow. The AFRL University Nanosat program [9], which has provided opportunities for educational research teams to participate in the development and launch of small satellites, has helped shape the HIFiRE philosophy with regard to coordination with academic research institutions.…”

Section: Programmatic Inspirationmentioning

confidence: 99%

Hypersonics into the 21st century: A perspective on AFOSR-sponsored research in aerothermodynamics

Schmisseur

2015

Progress in Aerospace Sciences

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“…The NASP team at McDonnell Douglas added grid adaptation to the NASA Langley supported CFL3DE and showed excellent comparison with historical flight data and NASP ground test data. Using the laminar heating flight data at Mach 20 from Reentry-F [11], a general guideline was established that a Y-plus (cell Reynolds number) value of 0.5 and under is good for heat transfer. The shock boundary grid adaptation needed no more than a 120 radial grid for good resolution.…”

Section: Cfd Lessons Learned In Nasp Hypersonicmentioning

confidence: 99%

Hypersonic Boundary-Layer Transition: Application to High-Speed Vehicle Design

Lau

2008

Journal of Spacecraft and Rockets

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This paper reports the boundary-layer transition characteristics of airbreathing hypersonic configurations and their impact on design environments. It discusses the evolution of the National Aerospace Plane configuration from an axisymmetric baseline to a wedgelike configuration where the transition mechanism is dominated by "natural" transition. The natural transition is characteristic of the "quiet" environment in free flight of smooth slender vehicles. This type of transition mechanism gradually evolves spatially in different modes that can be computed analytically and verified experimentally. The paper discusses the effect of leading-edge bluntness, surface wall temperature, and adverse pressure gradient in compression ramp on transition. The effect of freestream Mach number, Reynolds number, and angle of attack are also studied over the range of peak aerodynamic heating conditions of the National Aerospace Plane environment. The transition behavior was investigated using e N -type calculations based on a linear stability code known as the e Malik code.static pressure coefficient for the local condition c p = specific heat of air at constant pressure, Btu=lb m ; R c v = specific heat of air at constant volume, Btu=lb m ; R H aw = adiabatic wall enthalpy, Btu=lb m H t = total enthalpy, Btu=lb m H w = wall enthalpy, Btu=lb m h i = heat transfer coefficient for the local condition, Btu=ft 2 s; R L = length, inches or feet M = Mach number M e = boundary-edge Mach number Pr = Prandtl number p e = pressure at the boundary-layer edge, psia or psfa p i = pressure for the local condition, psia or psfa p t , p t1 = total or settling pressure, psia or psfa p t2 = pitot pressure in test section, psia or psfa p 1 , p = freestream static pressure, psia or psfa _ q w = heat transfer rate based on wall temperature, Btu=ft 2 s q 1 = freestream dynamic pressure, psi or psf R = radius, ft R g = gas constant per unit mass Re = Reynolds number Re = momentum thickness Reynolds number r = recovery factor St = Stanton number St 1 = freestream Stanton number T aw = adiabatic wall temperature, R T o = total temperature, R T t = total temperature, R T w = model wall temperature, R T 1 = freestream static temperature, R v 1 , v = freestream velocity, ft=s x=L = longitudinal position as a fraction of the reference length = angle of attack, degrees = angle of sideslip, degrees = ratio of specific heats, c p =c v = boundary-layer momentum thickness 1 = freestream dynamic viscosity, slugs=ft s e = dynamic viscosity at the boundary-layer edge, slugs=ft s w = dynamic viscosity at the wall, slugs=ft s = kinematic viscosity, slugs=ft s 1 = freestream density, slugs=ft 3 e = density at the boundary-layer edge, slugs=ft 3 w = density at the wall, slugs=ft 3 Subscripts aw = adiabatic wall condition e = boundary-layer edge condition effective = composite boundary-layer transition value used for vehicle design rn = nosetip/leading-edge (bluntness) t = total condition threshold = baseline boundary-layer transition value from simple correlation w = wa...

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Flight boundary layer transition measurements on a slender cone at Mach 20

Cited by 37 publications

References 1 publication

Enthalpy Effects on Hypervelocity Boundary-Layer Transition: Ground Test and Flight Data

Enthalpy Effects on Hypervelocity Boundary-Layer Transition: Ground Test and Flight Data

Hypersonics into the 21st century: A perspective on AFOSR-sponsored research in aerothermodynamics

Hypersonic Boundary-Layer Transition: Application to High-Speed Vehicle Design

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