HIFiRE-1 Flight Trajectory Estimation and Initial Experimental Results

Adamczak, David; Kimmel, Roger L.; Paull, A.; Alesi, Hans

doi:10.2514/6.2011-2358

Cited by 25 publications

(16 citation statements)

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“…Ref. 4 describes the HIFiRE-1 mission and system performance. Detailed findings from ground test experiments and related computations preceding the flight experiment are reported in Refs.…”

Section: Introductionmentioning

confidence: 99%

Transition Analysis for the HIFiRe-1 Flight Experiment

Choudhari

Chang

et al. 2011

41st AIAA Fluid Dynamics Conference and Exhibit

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The HIFiRE-1 flight experiment provided a valuable database pertaining to boundary layer transition over a 7-degree half-angle, circular cone model from supersonic to hypersonic Mach numbers, and a range of Reynolds numbers and angles of incidence. This paper reports the initial findings from the ongoing computational analysis pertaining to the measured in-flight transition behavior. Transition during the ascent phase at nearly zero degree angle of attack is dominated by second mode instabilities except in the vicinity of the cone meridian where a roughness element was placed midway along the length of the cone. The first mode instabilities were found to be weak at all trajectory points analyzed from the ascent phase. For times less than approximately 18.5 seconds into the flight, the peak amplification ratio for second mode disturbances is sufficiently small because of the lower Mach numbers at earlier times, so that the transition behavior inferred from the measurements is attributed to an unknown physical mechanism, potentially related to step discontinuities in surface height near the locations of a change in the surface material.

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“…Ref. 4 describes the HIFiRE-1 mission and system performance. Detailed findings from ground test experiments and related computations preceding the flight experiment are reported in Refs.…”

Section: Introductionmentioning

confidence: 99%

Transition Analysis for the HIFiRe-1 Flight Experiment

Choudhari

Chang

et al. 2011

41st AIAA Fluid Dynamics Conference and Exhibit

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“…25 A prior publication described the HIFiRE-1 mission. 26 The most notable complications in the mission with regard to its science objectives were failures of the on-board GPS and the exoatmospheric pointing maneuver, and drift in the cone thermocouples. The loss of the GPS meant that the vehicle altitude and velocity had to be reconstructed from existing data such as accelerometers, radar tracks, etc.…”

Section: Dimensions In MMmentioning

confidence: 99%

“…Ref. 26 describes development of the BET. The failure of the exoatmospheric pointing maneuver was a more serious malfunction, since it caused the vehicle to enter the atmosphere with an AoA as high as 40 degrees.…”

Section: Dimensions In MMmentioning

confidence: 99%

“…These roll rates, which are referenced to velocity, are slightly different from those extracted from the horizon sensors or magnetometers, which are earth-referenced. 26 Because AoA was higher during descent, a slightly more detailed assessment of roll angle was applied to this phase of flight. The description of this method is deferred to section 5.…”

Section: Figure 8 Cone Surface Pressure During Ascentmentioning

confidence: 99%

“…A prior paper describes the BEA and BET development. 26 The uncertainty in the freestream unit Reynolds number was estimated assuming contributions from uncertainties in altitude, velocity, and atmospheric properties. Uncertainties in altitude and velocity were assumed equal to the residual (original minus reconstructed flight data) of the BET.…”

Section: Figure 2 Hifire-1 As-flown Trajectorymentioning

confidence: 99%

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HIFiRE-1 and HIFiRE-5 Test Results

Kimmel¹,

Adamczak²,

Borg³

et al. 2014

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information AFRL/RQHF SPONSORING/MONITORING AGENCY REPORT NUMBER(S) AFRL-RQ-WP-TR-2014-0038 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution unlimited SUPPLEMENTARY NOTESPA Case Number: 88ABW-2014-3421; Clearance Date: 17 Jul 2014. ABSTRACTThe primary experiment for HIFiRE-1 was to measure boundary-layer transition in hypersonic flight on a 7 degree halfangle, axisymmetric cone with a 2.5 mm radius bluntness. A secondary experiment measured mean and fluctuating pressure, and heat transfer on a cylinder-33-degreee-flare geometry. The ascent provided smooth-body, low angle-ofattack, boundary-layer transition at Mach numbers greater than 5. The end of turbulent-to-laminar transition occurred at Reynolds numbers between 10.3 to 12.2 million. Second-mode N-factors of approximately 14 correlated transition. A diamond-shaped trip retained turbulent flow until reaching a roughness Reynolds number Rekk = 2200. During re-entry, transition was measured around the circumference of the cone at Reynolds numbers ranging from 3 million on the leeside to 5 million on the windward side. In the shock-boundary layer interaction, maximum sound pressure levels of 173 dB were recorded upstream of the flare, and 185 dB on the flare itself. The principal goal of HIFiRE-5 was to measure hypersonic boundary layer transition on an elliptic cone. The second stage booster failed to ignite, so the experiment reached a maximum Mach number of only 3. Nevertheless, supersonic pressure and temperature data were obtained under laminar and turbulent flow, and flight systems were validated. Traveling and stationary crossflow instabilities were clearly measured for HIFiRE-5 in ground test in a quiet flow tunnel. The frequency, phase speed, and wave angle were all in good agreement with computations.

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Hypersonic Air‐Breathing Flight Testing

2022

Scramjet Propulsion

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HIFiRE-1 Flight Trajectory Estimation and Initial Experimental Results

Cited by 25 publications

References 1 publication

Transition Analysis for the HIFiRe-1 Flight Experiment

Transition Analysis for the HIFiRe-1 Flight Experiment

HIFiRE-1 and HIFiRE-5 Test Results

Hypersonic Air‐Breathing Flight Testing

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