[
    {
        "id": "thesis:6021",
        "collection": "thesis",
        "collection_id": "6021",
        "cite_using_url": "https://resolver.caltech.edu/CaltechTHESIS:09032010-111033039",
        "primary_object_url": {
            "basename": "Hulcher_gd_1972.pdf",
            "content": "final",
            "filesize": 32999327,
            "license": "other",
            "mime_type": "application/pdf",
            "url": "/6021/1/Hulcher_gd_1972.pdf",
            "version": "v4.0.0"
        },
        "type": "thesis",
        "title": "Hypersonic Viscous-Inviscid Flow Interactions Including Boundary Layer Separation on a Flat Plate at Angle of Attack",
        "author": [
            {
                "family_name": "Hulcher",
                "given_name": "Gregory Don",
                "clpid": "Hulcher-Gregory-Don"
            }
        ],
        "thesis_advisor": [
            {
                "family_name": "Behrens",
                "given_name": "Wilhelm",
                "clpid": "Behrens-W"
            }
        ],
        "thesis_committee": [
            {
                "family_name": "Unknown",
                "given_name": "Unknown"
            }
        ],
        "local_group": [
            {
                "literal": "GALCIT"
            },
            {
                "literal": "div_eng"
            }
        ],
        "abstract": "Experimental measurements of mean flow properties over the leeward surface and in the near wake of an adiabatic thin flat plate at an angle of attack of \u03b1 = 15\u00b0 were obtained at Mach 6 and Reynolds number based on the chord length of 186,000. The leading edge thickness is the predominant variable which affects the pre-separation interaction region. The effects of the large windward pressure, which separates the boundary layer at \u2113/L \u2243 .7 are felt at points considerably forward of the separation point. The pressure rise in the separation region is similar to the rise on a flat plate-ramp model, and the data correlate according to Chapman's parameters. Also, the leeward side flow of the thin flat plate is found to be very similar to the flow over a wedge whose leeward side is inclined to the same angle. The wake centerline quantities behave similar to those behind a flat plate at zero angle of attack, but the streamwise gradients are less than those behind an inclined wedge. The flow appears to remain laminar throughout the entire field of measurement.",
        "doi": "10.7907/PZCP-FT88",
        "publication_date": "1972",
        "thesis_type": "engd",
        "thesis_year": "1972"
    },
    {
        "id": "thesis:6039",
        "collection": "thesis",
        "collection_id": "6039",
        "cite_using_url": "https://resolver.caltech.edu/CaltechTHESIS:09222010-130843966",
        "primary_object_url": {
            "basename": "Wu_jj_1971.pdf",
            "content": "final",
            "filesize": 3112468,
            "license": "other",
            "mime_type": "application/pdf",
            "url": "/6039/1/Wu_jj_1971.pdf",
            "version": "v4.0.0"
        },
        "type": "thesis",
        "title": "An Experimental Study of Hypersonic Wakes Behind Wedges at Angle of Attack",
        "author": [
            {
                "family_name": "Wu",
                "given_name": "Jiunn-Jenq",
                "clpid": "Wu-Jiunn-Jenq"
            }
        ],
        "thesis_advisor": [
            {
                "family_name": "Behrens",
                "given_name": "Wilhelm",
                "clpid": "Behrens-W"
            }
        ],
        "thesis_committee": [
            {
                "family_name": "Unknown",
                "given_name": "Unknown"
            }
        ],
        "local_group": [
            {
                "literal": "GALCIT"
            },
            {
                "literal": "div_eng"
            }
        ],
        "abstract": "Experimental measurements of mean flow properties of hypersonic wakes behind wedges of 20\u00b0 included angle were conducted for angles of attack up to 25\u00b0 at Mach number 6, with Reynolds number based on wedge base height ranging from 7000 to 55000. The near and far wake structures were determined, including streamlines and velocity profiles, over a downstream distance of 60 base heights. The base pressure is insensitive to angle of attack within about 17\u00b0. At higher incidence, flow separation occurs on the leeward surface. The far viscous wake (x/H Z 4) changes with increasing angle of attack mainly because of the increasing differences of the inviscid flow parameters at the leeward and windward edges of the viscous wake. Transition from laminar to turbulent flow moves upstream as \r\nangle of attack increases.",
        "doi": "10.7907/682B-HB46",
        "publication_date": "1971",
        "thesis_type": "engd",
        "thesis_year": "1971"
    }
]