HIFiRE-1: Payload Design, Manufacture, Ground Test, and Lessons Learned

43rd Fluid Dynamics Conference

Stanfield

2013

A scale model of the 2:1 elliptic cone HIFiRE-5 flight vehicle was used to investigate the traveling crossflow instability at Mach 6 in Purdue University's Mach-6 quiet wind tunnel. Traveling crossflow waves were measured with surface-mounted pressure sensors. The crossflow instability phase speed and wave angle were calculated from the cross spectra of three surface-mounted pressure sensors. Both quantities show good agreement with computational values from about 30-50 kHz. Repeated runs at the same initial condition show excellent repeatability in traveling crossflow wave properties, and give an estimate of the experimental uncertainty associated with this technique. Additionally, autobispectral analysis showed the onset and development of moderate nonlinear quadratic phase-locking prior to transition, but not for the peak traveling crossflow wave. The bicoherence achieved only moderate values. No traveling crossflow waves were observed when freestream noise levels were intentionally elevated, but transition occurred for a much lower Reynolds number. It appears that the traveling crossflow instability is not the primary transition mechanism in the noisy flow of Purdue's Mach 6 wind tunnel.

Section: Introductionmentioning

confidence: 99%

Traveling Crossflow Instability for HIFiRE-5 in a Quiet Hypersonic Wind Tunnel

Borg

43rd Fluid Dynamics Conference

Stanfield

2013

“…In order to prevent this, the vehicle is designed with one-piece leading edges, as shown in Figure 18. Sliding internal keys, similar to HFIRE-1, 14 lock the leading edges together with top and bottom clamshell pieces without external penetrating fasteners. …”

Section: Figure 15 Scaling Of Transition Due To 2d Roughnessmentioning

confidence: 99%

HIFiRE-5 Flight Vehicle Design

40th Fluid Dynamics Conference and Exhibit

Adamczak

Berger

et al. 2010

Self Cite

The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratories (AFRL)and Australian Defence Science and Technology Organization (DSTO). HIFiRE flight 5 is devoted to measuring transition on a three-dimensional body. This paper summarizes payload configuration, trajectory, vehicle stability limits and roughness tolerances. Results show that the proposed configuration is suitable for testing transition on a three-dimensional body. Transition is predicted to occur within the test window, and a design has been developed that will allow the vehicle to be manufactured within prescribed roughness tolerances. I. Nomenclature

“…Prior to flight, a series of experimental and numerical studies were performed to aid the design of the aerothermal experiments such as sensor selection and placement, and vehicle geometry and materials. [4][5][6][7][8][9][10][11][12][13][14][15] The cone, cylinder, and flare surfaces of the HIFiRE-1 payload were instrumented with many thermocouples, heat transfer gauges, and pressure transducers. During flight, the data from these transducers were digitized using a sampling scheme with a non-constant time interval between samples.…”

Section: Introductionmentioning

confidence: 99%

Compensation Method for the Estimation of the Autospectral Density Function of the Unevenly Spaced HIFiRE-1 Flight Data

Stanfield

43rd Fluid Dynamics Conference

2013

The time series data collected during the HIFiRE-1 flight experiment was sampled unevenly due to telemetry dropouts and the sampling scheme selected. Sampling unevenly results in frequency translation of power to artificial sidelobes. These sidelobes distort the real and imaginary components of the Fourier transform such that the spectrum of the sampled data no longer represents the spectrum of the physical process generating the data. These sidelobes can be eliminated by resampling the data onto an evenly spaced grid at the cost of under predicting the power of the higher frequency components in the data. In this paper, a compensation procedure is developed to recover the power loss caused by resampling. This compensation procedure is suitable for stochastic time series data having red-noise spectra such as the pressure fluctuations recorded underneath laminar and turbulent boundary layers. Nomenclaturea i = regression coefficient a 50 = overlap correlation constant b i = regression coefficient c xy = coherency D = location data point of a partition f = frequency, Hz This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. Fluid Dynamics and Co-located Conferences f 0 = fundamental frequency, Hz f c = Nyquist frequency, Hz G xx = autospectrum, Pa 2 / Hz G xy = cross-spectrum, Pa 2 / Hz K = number of partitions K eff = effective number of partitions L = number of data samples in a partition N = number data samples in a time series R = sum of squares t = time, sec t f = time used to account for different time origins of time series used in cross spectral analysis, sec t L = time at the end of a partition, sec T p = period, sec T R = sampling interval, sec w n = Hanning window function coefficients y n = time series data σ 2 = variance τ = time shift, sec ω = angular frequency, rad