The heat requirements for the icing protection of two radome configurations have been studied over a range of design icing conditions. Both the protection limits of a typical thermal protection system and the relative effects of the various icing variables have been determined. For full evaporation of all impinging water, an effective heat density of 14 watts per square inch was required. When a combination of the evaporation and running wet surface systems was employed, a heat requirement of 5 watts per square inch provided protection at severe icing and operating conditions
The problems associated with providing icing protection for the critical components of a typical tur...
Thermal anti-icing systems are commonly used to protect aircraft leading edges from a potentially ha...
radar operation, and the protect ion requirements f o r two radome con-f igura t ions. The radomes w...
Thermal ice protection systems use heat energy to prevent a dangerous buildup of ice on an aircraft....
A procedure proposed for use in the design of air-heated systems for the continuous prevention of ic...
Flight tests were made in natural icing conditions with two 8-ft-chord heated airfoils of different ...
Presented at 2018 Aviation Technology, Integration, and Operations Conference (AIAA 2018-4136)A ther...
The design analysis showed that the thermal requirements for the anti-icing systems of the wings, th...
A method is given for calculating the temperature that a surface, heated internally by air, will ass...
Research has been conducted to better understand the phenomena involved during operation of an aircr...
An investigation was conducted in the NACA Lewis icing research tunnel to determine the characterist...
A laboratory investigation was made on a Holley 1685-HB carburetor mounted on an R-2600-13 superchar...
A series of experimental tests were conducted in the NASA Lewis IRT on an electro-thermally heated N...
8490851PDFTech ReportDOT-TSC-FAA-81-24FAA-RD-81-112TS-15950IcingAirport surface traffic controlWindT...
The objective of the NASA aircraft icing research program is to develop and make available to indust...
The problems associated with providing icing protection for the critical components of a typical tur...
Thermal anti-icing systems are commonly used to protect aircraft leading edges from a potentially ha...
radar operation, and the protect ion requirements f o r two radome con-f igura t ions. The radomes w...
Thermal ice protection systems use heat energy to prevent a dangerous buildup of ice on an aircraft....
A procedure proposed for use in the design of air-heated systems for the continuous prevention of ic...
Flight tests were made in natural icing conditions with two 8-ft-chord heated airfoils of different ...
Presented at 2018 Aviation Technology, Integration, and Operations Conference (AIAA 2018-4136)A ther...
The design analysis showed that the thermal requirements for the anti-icing systems of the wings, th...
A method is given for calculating the temperature that a surface, heated internally by air, will ass...
Research has been conducted to better understand the phenomena involved during operation of an aircr...
An investigation was conducted in the NACA Lewis icing research tunnel to determine the characterist...
A laboratory investigation was made on a Holley 1685-HB carburetor mounted on an R-2600-13 superchar...
A series of experimental tests were conducted in the NASA Lewis IRT on an electro-thermally heated N...
8490851PDFTech ReportDOT-TSC-FAA-81-24FAA-RD-81-112TS-15950IcingAirport surface traffic controlWindT...
The objective of the NASA aircraft icing research program is to develop and make available to indust...
The problems associated with providing icing protection for the critical components of a typical tur...
Thermal anti-icing systems are commonly used to protect aircraft leading edges from a potentially ha...
radar operation, and the protect ion requirements f o r two radome con-f igura t ions. The radomes w...