Pressure and Heat Transfer Measurements for Hypersonic Flows over Expansion Corners and Ahead of Ramps Part II: Mach 5 Pressure Data for Flows Ahead of Ramps: :Part of an Investigation of Hypersonic Flow Separation and Control Characteristics
Report Number: ASD TDR 63-679 Part 2
Author: Kaufman, Louis G.
Corporate Author: Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1963-09
Pages: 227
Contract: AF 33(616)-8130
Project: 8219
Task: 821902
AD Number: AD0421859
Abstract: The abstract for this report is either unavailable or has yet to be entered
Provenance: AFRL/VACA
Other options for obtaining this report
Via the Defense Technical Information Center (DTIC): A record for this report, and possibly a full-image download of the report, exists at DTIC Via National Technical Information Service: This report may have been digitized and made freely available for public download, or made publicly available for purchase by the National Technical Information Service through their online database, the National Technical Reports Library Indications of Public Availability No digital image of an index entry indicating public availability is currently available There has been no verification of an indication of public availability from an inside cover statementRelated Reports
This report has the following parts/volumes:
-
Pressure and Heat Transfer Measurements for Hypersonic Flows over Expansion Corners and Ahead of Ramps Part I: Mach 5 and 8 Data for Expansion Corner Flows: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics
ASD TDR 63-679 Part 1 -
Pressure and Heat Transfer Measurements for Flows Ahead of Ramps Part III: Mach 8 Pressure Data for Flows Ahead of Ramps: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics
ASD TDR 63-679 Part 3 -
Pressure and Heat Transfer Measurements for Hypersonic Flows over Expansion Corners and Ahead of Ramps. Part IV: Mach 8 Heat Transfer Data for Flows Ahead of Ramps: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics
ASD TDR 63-679 Part 4