Studies of Aerothermal Loads Generated in Regions of ShockIShock Interaction in Hypersonic Flow. Holden, M., Wieting, A., Moselle, J., Wietingi, A., Moselle, R, & Glass, C In 1988. doi abstract bibtex A study is presented of t h e aerothermal characteristics of regions of two-dimensional shocklshock interaction generated by the incidence of single and multiple shocks onto t h e bow shock ahead of a spanwise cylinder. Detailed measurements of the distribution of heat transfer and pressure were made in t h e peak heating regions around the cylinder for a number of shocklshock interactions which induced the greatest "interference heating". The studies were conducted in t h e 48" and 96" Shock Tunnels a t Calspan a t Mach numbers from 8 t o 19 with a two-dimensional wedge shock generatorttraverse cylinder model. The severity of the heat transfer gradients generated in the interaction regions requires an insulated model surface to prevent distortion by lateral heat conduction. However, models with low surface conductivity also result in large surface temperature rises in these inieiactjng flows, thereby presenting problems with data analysis. For transitional flows, the measurements demonstrated a large increase in the aerothermal loads with increasing Mach numbers which cannot be predicted by simple phenomenological models. However, t h e flow configurations t h a t exhibit t h e largest heating loads also appear to be inherently unstable and, therefore, cannot be predicted in detail using simple flow models. Flows with transition in the shear layer or boundary layer (which occurs a t relatively low Reynolds numbers (lo4)) also cannot be accurately predicted. The studies with multiple incident shocks demonstrate t h a t t h e largest aerothermal Ioads are generated on t h e cylinder when the shacks coalesce before they a r e incident on the bow shock. While a number of interesting flow fields are generated when two shocks a r e separately incident on the cylinder shock, the peak heating loads remain less than if they coalesce ahead of the bow shock. The presence of transition in t h e flow makes it difficult to predict aerothermal loads generated by multiple shock/shock interactions.
@inproceedings{holden1988,
title = {Studies of {Aerothermal} {Loads} {Generated} in {Regions} of {ShockIShock} {Interaction} in {Hypersonic} {Flow}},
doi = {10.2514/6.1988-477},
abstract = {A study is presented of t h e aerothermal characteristics of regions of two-dimensional shocklshock interaction generated by the incidence of single and multiple shocks onto t h e bow shock ahead of a spanwise cylinder. Detailed measurements of the distribution of heat transfer and pressure were made in t h e peak heating regions around the cylinder for a number of shocklshock interactions which induced the greatest "interference heating". The studies were conducted in t h e 48" and 96" Shock Tunnels a t Calspan a t Mach numbers from 8 t o 19 with a two-dimensional wedge shock generatorttraverse cylinder model. The severity of the heat transfer gradients generated in the interaction regions requires an insulated model surface to prevent distortion by lateral heat conduction. However, models with low surface conductivity also result in large surface temperature rises in these inieiactjng flows, thereby presenting problems with data analysis. For transitional flows, the measurements demonstrated a large increase in the aerothermal loads with increasing Mach numbers which cannot be predicted by simple phenomenological models. However, t h e flow configurations t h a t exhibit t h e largest heating loads also appear to be inherently unstable and, therefore, cannot be predicted in detail using simple flow models. Flows with transition in the shear layer or boundary layer (which occurs a t relatively low Reynolds numbers (lo4)) also cannot be accurately predicted. The studies with multiple incident shocks demonstrate t h a t t h e largest aerothermal Ioads are generated on t h e cylinder when the shacks coalesce before they a r e incident on the bow shock. While a number of interesting flow fields are generated when two shocks a r e separately incident on the cylinder shock, the peak heating loads remain less than if they coalesce ahead of the bow shock. The presence of transition in t h e flow makes it difficult to predict aerothermal loads generated by multiple shock/shock interactions.},
author = {Holden, MS and Wieting, Ar and Moselle, JR and Wietingi, Ar and Moselle, R and Glass, C},
year = {1988},
}
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{"_id":"aXwdJ8jHNiYMd7NjA","bibbaseid":"holden-wieting-moselle-wietingi-moselle-glass-studiesofaerothermalloadsgeneratedinregionsofshockishockinteractioninhypersonicflow-1988","author_short":["Holden, M.","Wieting, A.","Moselle, J.","Wietingi, A.","Moselle, R","Glass, C"],"bibdata":{"bibtype":"inproceedings","type":"inproceedings","title":"Studies of Aerothermal Loads Generated in Regions of ShockIShock Interaction in Hypersonic Flow","doi":"10.2514/6.1988-477","abstract":"A study is presented of t h e aerothermal characteristics of regions of two-dimensional shocklshock interaction generated by the incidence of single and multiple shocks onto t h e bow shock ahead of a spanwise cylinder. Detailed measurements of the distribution of heat transfer and pressure were made in t h e peak heating regions around the cylinder for a number of shocklshock interactions which induced the greatest \"interference heating\". The studies were conducted in t h e 48\" and 96\" Shock Tunnels a t Calspan a t Mach numbers from 8 t o 19 with a two-dimensional wedge shock generatorttraverse cylinder model. The severity of the heat transfer gradients generated in the interaction regions requires an insulated model surface to prevent distortion by lateral heat conduction. However, models with low surface conductivity also result in large surface temperature rises in these inieiactjng flows, thereby presenting problems with data analysis. For transitional flows, the measurements demonstrated a large increase in the aerothermal loads with increasing Mach numbers which cannot be predicted by simple phenomenological models. However, t h e flow configurations t h a t exhibit t h e largest heating loads also appear to be inherently unstable and, therefore, cannot be predicted in detail using simple flow models. Flows with transition in the shear layer or boundary layer (which occurs a t relatively low Reynolds numbers (lo4)) also cannot be accurately predicted. The studies with multiple incident shocks demonstrate t h a t t h e largest aerothermal Ioads are generated on t h e cylinder when the shacks coalesce before they a r e incident on the bow shock. While a number of interesting flow fields are generated when two shocks a r e separately incident on the cylinder shock, the peak heating loads remain less than if they coalesce ahead of the bow shock. The presence of transition in t h e flow makes it difficult to predict aerothermal loads generated by multiple shock/shock interactions.","author":[{"propositions":[],"lastnames":["Holden"],"firstnames":["MS"],"suffixes":[]},{"propositions":[],"lastnames":["Wieting"],"firstnames":["Ar"],"suffixes":[]},{"propositions":[],"lastnames":["Moselle"],"firstnames":["JR"],"suffixes":[]},{"propositions":[],"lastnames":["Wietingi"],"firstnames":["Ar"],"suffixes":[]},{"propositions":[],"lastnames":["Moselle"],"firstnames":["R"],"suffixes":[]},{"propositions":[],"lastnames":["Glass"],"firstnames":["C"],"suffixes":[]}],"year":"1988","bibtex":"@inproceedings{holden1988,\n\ttitle = {Studies of {Aerothermal} {Loads} {Generated} in {Regions} of {ShockIShock} {Interaction} in {Hypersonic} {Flow}},\n\tdoi = {10.2514/6.1988-477},\n\tabstract = {A study is presented of t h e aerothermal characteristics of regions of two-dimensional shocklshock interaction generated by the incidence of single and multiple shocks onto t h e bow shock ahead of a spanwise cylinder. Detailed measurements of the distribution of heat transfer and pressure were made in t h e peak heating regions around the cylinder for a number of shocklshock interactions which induced the greatest \"interference heating\". The studies were conducted in t h e 48\" and 96\" Shock Tunnels a t Calspan a t Mach numbers from 8 t o 19 with a two-dimensional wedge shock generatorttraverse cylinder model. The severity of the heat transfer gradients generated in the interaction regions requires an insulated model surface to prevent distortion by lateral heat conduction. However, models with low surface conductivity also result in large surface temperature rises in these inieiactjng flows, thereby presenting problems with data analysis. For transitional flows, the measurements demonstrated a large increase in the aerothermal loads with increasing Mach numbers which cannot be predicted by simple phenomenological models. However, t h e flow configurations t h a t exhibit t h e largest heating loads also appear to be inherently unstable and, therefore, cannot be predicted in detail using simple flow models. Flows with transition in the shear layer or boundary layer (which occurs a t relatively low Reynolds numbers (lo4)) also cannot be accurately predicted. The studies with multiple incident shocks demonstrate t h a t t h e largest aerothermal Ioads are generated on t h e cylinder when the shacks coalesce before they a r e incident on the bow shock. While a number of interesting flow fields are generated when two shocks a r e separately incident on the cylinder shock, the peak heating loads remain less than if they coalesce ahead of the bow shock. The presence of transition in t h e flow makes it difficult to predict aerothermal loads generated by multiple shock/shock interactions.},\n\tauthor = {Holden, MS and Wieting, Ar and Moselle, JR and Wietingi, Ar and Moselle, R and Glass, C},\n\tyear = {1988},\n}\n\n\n\n","author_short":["Holden, M.","Wieting, A.","Moselle, J.","Wietingi, A.","Moselle, R","Glass, C"],"key":"holden1988","id":"holden1988","bibbaseid":"holden-wieting-moselle-wietingi-moselle-glass-studiesofaerothermalloadsgeneratedinregionsofshockishockinteractioninhypersonicflow-1988","role":"author","urls":{},"metadata":{"authorlinks":{}}},"bibtype":"inproceedings","biburl":"https://bibbase.org/zotero-group/khanquist/4882481","dataSources":["qwkM8ZucCwtxbnXfc"],"keywords":[],"search_terms":["studies","aerothermal","loads","generated","regions","shockishock","interaction","hypersonic","flow","holden","wieting","moselle","wietingi","moselle","glass"],"title":"Studies of Aerothermal Loads Generated in Regions of ShockIShock Interaction in Hypersonic Flow","year":1988}