FOREWORD This report presents the results of a study concerning the acquisition and reduction of thin-skin heating data from the Air Force Flight Dynamics Laboratory's High Temperature Facility. The work was done in-hous;e under Project 1366 "Aeroperformance and Aeroheating Technology", Task 136603 "Aerodynamic Heating to Military Vehicles " and was conducted from June to October 1973. This technical memorandum has been reviewed and approved. \c-„PHILIP P. ANTONATOS ' Chief, Flight Mechanics Division AF Flight Dynamics Laboratory ii This report presents a method to acquire and reduce thin-skin heat transfer data from the AFFDL High Temperature Facility. The calculatio
"An experimental investigation was conducted at a test-section Mach number of 4.95 and a stagnation ...
The EFT-1 Avcoat heatshield was instrumented with 34 plugs containing multiple thermocouples in-dept...
Numerical method for reducing data from thick calorimeter to determine heating rate to calorimeter s...
Thesis (Ph.D.)--Boston University.An analysis is given which treats experimental heat-transfer data ...
Hypersonic missiles re-entering the atmosphere are subjected to severe aerodynamic heating. In order...
Aerodynamic heat flux determined within thermally thick walls for case of rapidly rising heat rate
Abstract: The method presented in NACA TN 2692 for evaluating the skin friction of a turbulent bound...
The evaluation of the effects of altitude on forced air convective cooling is studied experimentally...
This report describes a method that can calculate transient aerodynamic heating and transient surfac...
The design analysis showed that the thermal requirements for the anti-icing systems of the wings, th...
Detailed aeroheating information is critical to the successful design of a thermal protection system...
This dissertation describes the use of permanent-change thermal paints as a technique for global sur...
Rockets, Satellites and other space-craft moving at supersonic and hypersonic speeds through the atm...
Sonic boom minimization by application of heat or force fields to airplane airflow.Prepared at Langl...
The knowledge of air temperature has always been an. essential part of any flight test records for ...
"An experimental investigation was conducted at a test-section Mach number of 4.95 and a stagnation ...
The EFT-1 Avcoat heatshield was instrumented with 34 plugs containing multiple thermocouples in-dept...
Numerical method for reducing data from thick calorimeter to determine heating rate to calorimeter s...
Thesis (Ph.D.)--Boston University.An analysis is given which treats experimental heat-transfer data ...
Hypersonic missiles re-entering the atmosphere are subjected to severe aerodynamic heating. In order...
Aerodynamic heat flux determined within thermally thick walls for case of rapidly rising heat rate
Abstract: The method presented in NACA TN 2692 for evaluating the skin friction of a turbulent bound...
The evaluation of the effects of altitude on forced air convective cooling is studied experimentally...
This report describes a method that can calculate transient aerodynamic heating and transient surfac...
The design analysis showed that the thermal requirements for the anti-icing systems of the wings, th...
Detailed aeroheating information is critical to the successful design of a thermal protection system...
This dissertation describes the use of permanent-change thermal paints as a technique for global sur...
Rockets, Satellites and other space-craft moving at supersonic and hypersonic speeds through the atm...
Sonic boom minimization by application of heat or force fields to airplane airflow.Prepared at Langl...
The knowledge of air temperature has always been an. essential part of any flight test records for ...
"An experimental investigation was conducted at a test-section Mach number of 4.95 and a stagnation ...
The EFT-1 Avcoat heatshield was instrumented with 34 plugs containing multiple thermocouples in-dept...
Numerical method for reducing data from thick calorimeter to determine heating rate to calorimeter s...