Influence of Thermal Non-equilibrium on Nozzle Flow Condition of High Enthalpy Shock Tunnel HIEST

Takahashi, M.; Kodera, Masatoshi; Itoh, Katsuhiro; Komuro, Tomoyuki; Sato, K.; Tanno, Hideyuki

doi:10.2514/6.2009-7267

Cited by 23 publications

(11 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…We choose the low enthalpy condition of aeroheating measurements on HTV-R capsule with forced transition by Tanno et al 17 These upstream conditions are calculated by the JAXA in-house nozzle flow code. 39 The cell interface values near the shock waves are interpolated by MUSCL, while in other region the WENO interpolation method is used. Figure 10 shows the computational grid and the enlarged view around the trip is shown in Fig.…”

Section: Iiib Flowfield Over Htv-r Capsule and Heat Flux Around A Tripmentioning

confidence: 99%

LES Computation of Turbulent Heat Flux on Reentry Capsule Afterbody with Forced Transition

Ishihara

Ogino²,

Ohnishi³

et al. 2015

53rd AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

A high order CFD code was developed for LES computation of turbulent heat flux in hypersonic flow. Aeroheating measurement tests with forced transition on an Apollo capsule model and an HTV-R which was a manned space capsule under development by JAXA were performed by the free-piston shock tunnel HIEST in JAXA Kakuda Space Center. Measured data set indicate that heat flux on the forebody of the Apollo capsule model was 1.5-2 times larger than one in laminar flow. On the other hand, the heat flux on the afterbody of HTV-R became significantly larger. Furthermore, in the separation region which exists afterbody of capsules, the Baldwin-Lomax model which can reproduce turbulent heat flux in the attached flow, tends to underestimate. In order to reproduce the turbulent heat flux on the after body by numerical simulation, high order CFD code towards LES in hypersonic flow is needed. Since the robustness near the shock and high resolution in the boundary layer is needed for LES in hypersonic flow, improved WENO method is employed. We calculated the hypersonic flow (M∞ = 17) around cylinder and investigated the robustness for strong shock by the method. Smooth pressure distribution was obtained agree well with the calculated heat flux by NASA LAURA code. Our developed code applied to the hypersonic flowfield around HTV-R with a trip and the heat flux was examined.

show abstract

Section: Iiib Flowfield Over Htv-r Capsule and Heat Flux Around A Tripmentioning

confidence: 99%

LES Computation of Turbulent Heat Flux on Reentry Capsule Afterbody with Forced Transition

Ishihara

Ogino²,

Ohnishi³

et al. 2015

53rd AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

show abstract

“…Table 1 shows the test-flow conditions, which were calculated with equilibrium shock tube code 7 , followed by an axis-symmetrical JAXA in-house nozzle flow code 8 . The present test condition was low enthalpy, in which the flow could be judged as a perfect gas, enabling measurements to be compared directly with the results from other conventional blow-down wind tunnels to evaluate the accuracy of the technique.…”

Section: Test-flow Conditionmentioning

confidence: 99%

Free-flight aerodynamic test of elliptic cone in Shock Tunnel

Tanno

Komuro²,

Sato³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

Self Cite

View full text Add to dashboard Cite

A free-flight measurement technique was applied to an aerodynamic test with a largescale test model in the JAXA-HIEST free-piston shock tunnel and a preliminary aerodynamic force measurement conducted to study the feasibility of the technique with an elliptic cone 880mm length long and 23.5kg in mass. The cone model was a full-scale model of the HIFiRE-5 (Hypersonic International Flight Research and Experiment) payload, a model with on-board instruments such as accelerometers and miniature data recorders specially designed to facilitate this free-flight force measurement technique. During the short HIEST test period, the cone model flew in the hypersonic test flow and axial and normal forces were successfully measured at a 7-degree angle of attack and under low stagnation condition (Stagnation enthalpy was 3MJ/kg and stagnation pressure was 14MPa), with conditions equivalent to a Mach 8 flight. The present test demonstrated that the free-flight measuring technique in shock tunnels could be successfully applied to a test model almost one meter in size, equivalent to the dimensions of general flight test models using sounding rockets. The technique has the potential to drastically reduce down the cost of experiments used to develop scramjet-powered vehicles under hypersonic conditions.

show abstract

“…In all the HIEST test campaigns reported in this article, two tunnel conditions were selected. Table 1 shows the test-flow conditions, which were calculated with an axis-symmetrical in-house nozzle flow code 10 . The first condition was low-enthalpy, in which the flow could be approximated as a perfect gas, enabling measurements to be compared directly with results from the conventional blow-down wind tunnel JAXA-HWT2 11 to evaluate the accuracy of the technique.…”

Section: E Test Flow Conditionmentioning

confidence: 99%

Free-flight aerodynamic tests of reentry vehicles in high-temperature real-gas flow (Invited)

Tanno

Sato

Komuro

et al. 2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

Self Cite

View full text Add to dashboard Cite

Aerodynamic tests conducted in the HIEST free-piston high-enthalpy shock tunnel were reported. A novel multi-component force-measurement technique was implemented, which involved the test model being completely non-restrained for the duration of the test and thus experiencing free-flight conditions for a period in the order of milliseconds. Compared with conventional free-flight techniques, the present one has the advantage of no aerodynamic interference with the model support system and less variation in the model position and attitude during the test. The measurement accuracy and precision of the technique were compared to a conventional blow-down wind tunnel and evaluated in a HIEST test campaign with a blunted cone. During the test campaign, the pitching-moment coefficient under the HIEST high-enthalpy condition differed significantly from that of low enthalpy, which was considered attributable to high-temperature real-gas effects. The technique has already been applied to a HIEST test campaign for the Japanese HTV-R re-entry capsule to determine its trim angle at re-entry. Moreover, the technique was also adopted to measure the body flap (elevon) efficiency of the HYFLEX lifting body. NomenclatureAOA = Angle of attack CA = Axial force coefficient CN = Normal force coefficient CMy = Pitching moment coefficient P 0 = Stagnation pressure P Pitot = Free-stream Pitot pressure PI = Prediction interval X = Model displacement (x-direction) Y = Model displacement (y-direction)  = Standard deviation *

show abstract

Influence of Thermal Non-equilibrium on Nozzle Flow Condition of High Enthalpy Shock Tunnel HIEST

Cited by 23 publications

References 9 publications

LES Computation of Turbulent Heat Flux on Reentry Capsule Afterbody with Forced Transition

LES Computation of Turbulent Heat Flux on Reentry Capsule Afterbody with Forced Transition

Free-flight aerodynamic test of elliptic cone in Shock Tunnel

Free-flight aerodynamic tests of reentry vehicles in high-temperature real-gas flow (Invited)

Contact Info

Product

Resources

About