@inproceedings{anthis2026,
	title = {Investigation of {Supersonic} {Jet} in {Mach} 4 {Crossflow} on a {Generic} {Finned} {Ogive}-{Cylinder}},
	doi = {10.2514/6.2026-1945},
	abstract = {The interaction of a Mach 3 jet on an ogive-cylinder with fins in a Mach 4 crossflow was studied. The test article was derived from the Army Research Lab's (ARL) Laboratory Test Vehicle (LTV) to provide a generic test case for experimental and computational investigations. The sensitivities to the jet exit pressure (i.e., jet momentum ratio) and vehicle yaw angles were explored. Measurements of the jet interaction included z-type Schlieren, mean and dynamic surface pressure, infrared thermography (IR), and oil flow visualization (OFV). These data were supplemented with SU2 simulations, utilizing Reynolds Averaged Navier-Stokes (RANS) with Shear Stress Transport (SST) turbulence model. Increasing jet momentum ratio resulted in a stronger jet bow shock, a jet that penetrated deeper into the freestream, and the growth of the separated region upstream of the jet. The time-averaged centerline surface pressure distributions show a pressure rise and drop just upstream and downstream of the jet, respectively. The magnitudes of these pressure extrema increased with jet momentum ratio. Computational pressure contours revealed a high-pressure crescent-shaped region wrapping around the upstream side of the model. OFV and IR measurements revealed this region corresponds to a region of separated flow generated by the interaction. This region grows both in the upstream direction and in the azimuthal direction with increasing momentum ratio. Additionally, the jet bow shock foot appeared to follow the high-pressure crescent region. It impinged on the fins; the impingement location moved upstream with increased momentum ratio. The interaction between the separated flow region and the fin generated hot spots near the base of each fin. Downstream of the jet, the centerline pressure recovery region lengthened in the streamwise direction with increasing jet momentum ratio. Pressure spectra revealed coherent frequencies that appeared to shift with momentum ratio. There is evidence of coherent structures originating upstream of the jet that propagate downstream into the wake. Forces and moments were extracted from simulation data and used to estimate amplification factors and their sensitivity to jet momentum ratio and vehicle yaw. Normal force and pitching moment amplification decreased and increased, respectively, as jet momentum ratio increased. For a given momentum ratio, a decrease in both amplification factors was observed with increasing yaw angle.},
	urldate = {2026-01-23},
	booktitle = {{AIAA} {SCITECH} 2026 {Forum}},
	publisher = {AIAA Paper 2026-1945},
	author = {Anthis, Roman and Pierce, Matthew K. and Singh, Ashish and Hanquist, Kyle M. and Threadgill, James A. and Gray, Patrick D.},
	year = {2026},
	keywords = {own},
}

{"_id":"j7fonPDNNb9sC6uCd","bibbaseid":"anthis-pierce-singh-hanquist-threadgill-gray-investigationofsupersonicjetinmach4crossflowonagenericfinnedogivecylinder-2026","author_short":["Anthis, R.","Pierce, M. K.","Singh, A.","Hanquist, K. M.","Threadgill, J. A.","Gray, P. D."],"bibdata":{"bibtype":"inproceedings","type":"inproceedings","title":"Investigation of Supersonic Jet in Mach 4 Crossflow on a Generic Finned Ogive-Cylinder","doi":"10.2514/6.2026-1945","abstract":"The interaction of a Mach 3 jet on an ogive-cylinder with fins in a Mach 4 crossflow was studied. The test article was derived from the Army Research Lab's (ARL) Laboratory Test Vehicle (LTV) to provide a generic test case for experimental and computational investigations. The sensitivities to the jet exit pressure (i.e., jet momentum ratio) and vehicle yaw angles were explored. Measurements of the jet interaction included z-type Schlieren, mean and dynamic surface pressure, infrared thermography (IR), and oil flow visualization (OFV). These data were supplemented with SU2 simulations, utilizing Reynolds Averaged Navier-Stokes (RANS) with Shear Stress Transport (SST) turbulence model. Increasing jet momentum ratio resulted in a stronger jet bow shock, a jet that penetrated deeper into the freestream, and the growth of the separated region upstream of the jet. The time-averaged centerline surface pressure distributions show a pressure rise and drop just upstream and downstream of the jet, respectively. The magnitudes of these pressure extrema increased with jet momentum ratio. Computational pressure contours revealed a high-pressure crescent-shaped region wrapping around the upstream side of the model. OFV and IR measurements revealed this region corresponds to a region of separated flow generated by the interaction. This region grows both in the upstream direction and in the azimuthal direction with increasing momentum ratio. Additionally, the jet bow shock foot appeared to follow the high-pressure crescent region. It impinged on the fins; the impingement location moved upstream with increased momentum ratio. The interaction between the separated flow region and the fin generated hot spots near the base of each fin. Downstream of the jet, the centerline pressure recovery region lengthened in the streamwise direction with increasing jet momentum ratio. Pressure spectra revealed coherent frequencies that appeared to shift with momentum ratio. There is evidence of coherent structures originating upstream of the jet that propagate downstream into the wake. Forces and moments were extracted from simulation data and used to estimate amplification factors and their sensitivity to jet momentum ratio and vehicle yaw. Normal force and pitching moment amplification decreased and increased, respectively, as jet momentum ratio increased. For a given momentum ratio, a decrease in both amplification factors was observed with increasing yaw angle.","urldate":"2026-01-23","booktitle":"AIAA SCITECH 2026 Forum","publisher":"AIAA Paper 2026-1945","author":[{"propositions":[],"lastnames":["Anthis"],"firstnames":["Roman"],"suffixes":[]},{"propositions":[],"lastnames":["Pierce"],"firstnames":["Matthew","K."],"suffixes":[]},{"propositions":[],"lastnames":["Singh"],"firstnames":["Ashish"],"suffixes":[]},{"propositions":[],"lastnames":["Hanquist"],"firstnames":["Kyle","M."],"suffixes":[]},{"propositions":[],"lastnames":["Threadgill"],"firstnames":["James","A."],"suffixes":[]},{"propositions":[],"lastnames":["Gray"],"firstnames":["Patrick","D."],"suffixes":[]}],"year":"2026","keywords":"own","bibtex":"@inproceedings{anthis2026,\n\ttitle = {Investigation of {Supersonic} {Jet} in {Mach} 4 {Crossflow} on a {Generic} {Finned} {Ogive}-{Cylinder}},\n\tdoi = {10.2514/6.2026-1945},\n\tabstract = {The interaction of a Mach 3 jet on an ogive-cylinder with fins in a Mach 4 crossflow was studied. The test article was derived from the Army Research Lab's (ARL) Laboratory Test Vehicle (LTV) to provide a generic test case for experimental and computational investigations. The sensitivities to the jet exit pressure (i.e., jet momentum ratio) and vehicle yaw angles were explored. Measurements of the jet interaction included z-type Schlieren, mean and dynamic surface pressure, infrared thermography (IR), and oil flow visualization (OFV). These data were supplemented with SU2 simulations, utilizing Reynolds Averaged Navier-Stokes (RANS) with Shear Stress Transport (SST) turbulence model. Increasing jet momentum ratio resulted in a stronger jet bow shock, a jet that penetrated deeper into the freestream, and the growth of the separated region upstream of the jet. The time-averaged centerline surface pressure distributions show a pressure rise and drop just upstream and downstream of the jet, respectively. The magnitudes of these pressure extrema increased with jet momentum ratio. Computational pressure contours revealed a high-pressure crescent-shaped region wrapping around the upstream side of the model. OFV and IR measurements revealed this region corresponds to a region of separated flow generated by the interaction. This region grows both in the upstream direction and in the azimuthal direction with increasing momentum ratio. Additionally, the jet bow shock foot appeared to follow the high-pressure crescent region. It impinged on the fins; the impingement location moved upstream with increased momentum ratio. The interaction between the separated flow region and the fin generated hot spots near the base of each fin. Downstream of the jet, the centerline pressure recovery region lengthened in the streamwise direction with increasing jet momentum ratio. Pressure spectra revealed coherent frequencies that appeared to shift with momentum ratio. There is evidence of coherent structures originating upstream of the jet that propagate downstream into the wake. Forces and moments were extracted from simulation data and used to estimate amplification factors and their sensitivity to jet momentum ratio and vehicle yaw. Normal force and pitching moment amplification decreased and increased, respectively, as jet momentum ratio increased. For a given momentum ratio, a decrease in both amplification factors was observed with increasing yaw angle.},\n\turldate = {2026-01-23},\n\tbooktitle = {{AIAA} {SCITECH} 2026 {Forum}},\n\tpublisher = {AIAA Paper 2026-1945},\n\tauthor = {Anthis, Roman and Pierce, Matthew K. and Singh, Ashish and Hanquist, Kyle M. and Threadgill, James A. and Gray, Patrick D.},\n\tyear = {2026},\n\tkeywords = {own},\n}\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n\n","author_short":["Anthis, R.","Pierce, M. K.","Singh, A.","Hanquist, K. M.","Threadgill, J. A.","Gray, P. D."],"key":"anthis2026","id":"anthis2026","bibbaseid":"anthis-pierce-singh-hanquist-threadgill-gray-investigationofsupersonicjetinmach4crossflowonagenericfinnedogivecylinder-2026","role":"author","urls":{},"keyword":["own"],"metadata":{"authorlinks":{}}},"bibtype":"inproceedings","biburl":"https://bibbase.org/zotero-group/khanquist/4882481","dataSources":["qwkM8ZucCwtxbnXfc"],"keywords":["own"],"search_terms":["investigation","supersonic","jet","mach","crossflow","generic","finned","ogive","cylinder","anthis","pierce","singh","hanquist","threadgill","gray"],"title":"Investigation of Supersonic Jet in Mach 4 Crossflow on a Generic Finned Ogive-Cylinder","year":2026}