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An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 5: Effect of Thermal System on Airplane Cruise Performance

Description: Report presenting flight tests conducted to evaluate the effect of a thermal ice prevention system on the aerodynamic performance of a C-46 cargo airplane. The installation of the thermal ice-prevention system was found to reduce the indicated airspeed by about 6 miles per hour. Results regarding the overall performance change resulting from the installation of the thermal system, reduction of power attributed to heat-exchanger exhaust-gas back pressure, reduction of power attributed to the int… more
Date: May 1945
Creator: Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 4: Results of Flight Tests in Dry-Air and Natural-Icing Conditions

Description: Report presenting an investigation of a thermal ice-prevention system for a C-46 cargo airplane, which involved flight tests in dry-air and natural-icing conditions at two different laboratories. The purpose of the investigation was to determine the effectiveness of the C-46 airplane ice-prevention system and to continue the develop of thermal ice-prevention equipment. Results regarding the wing outer panel, wing tips, wing center panel, horizontal stabilizers, vertical fin, windshields, ice-re… more
Date: February 1945
Creator: Selna, James; Neel, Carr B., Jr. & Zeiller, E. Lewis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of a Thermal Ice-Prevention System for a C-46 Cargo Airplane 6: Dry-Air Performance of Thermal System at Several Twin- and Single-Engine Operating Conditions at Various Altitudes

Description: Report presenting flight tests to establish the dry-air-performance characteristics of a thermal ice-prevention system at various operating conditions and altitudes. Results regarding twin-engine tests and single-engine tests of characteristics such as skin temperatures and location of heating are provided.
Date: May 1945
Creator: Selna, James & Kees, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of Several Exhaust-Gas-to-Air Heat Exchangers in the B-17F Airplane

Description: Report presenting flight testing of seven exhaust-gas-to-air heat exchangers on a B-17F airplane to determine their performance characteristics and to investigate their flame-suppression qualities. Testing was conducted to secure performance data of heat exchangers which might be suitable for use in the thermal ice-prevention and cabin-heating system of the heavy bomber-type airplanes.
Date: April 1944
Creator: Look, Bonne C. & Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Method for Calculating the Heat Required for the Prevention of Fog Formations on the Inside Surfaces of Single-Panel Bullet-Resisting Windshields During Diving Flight

Description: Note presenting an investigation to provide a means for calculating the heat required for the prevention of fog formations on the inside surfaces of single-panel bullet-resisting windshields during diving flight. An analysis was made to provide relationships for the heat required considering the transient heating of the windshield during diving flight.
Date: July 1947
Creator: Selna, James & Zerbe, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation of the Thermal Performance of an Air-Heated Propeller

Description: Note presenting the thermal performance of an air-heated propeller, installed on a test airplane, as evaluated by observations of the ice-prevention properties of the propeller during flight in natural-icing conditions and by the collection of thermal data on the propeller during flight in clear air and in clouds at temperatures above freezing. The results indicated that the air-heated-propeller installation tested would offer little or no protection to the leading-edge regions of the propeller… more
Date: April 1947
Creator: Darsow, John F. & Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Investigation of the Thermal Performance of Air Heated Propeller

Description: Note presenting the thermal performance of an air-heated propeller, installed on a test airplane, as evaluated by observations of the ice-prevention properties of the propeller during flight in natural icing conditions and by the collection of thermal data on the propeller during flight in clear air and in clouds at temperatures above freezing. The results indicated that the air-heated-propeller installation tested would offer little or no protection to the leading-edge regions of the propeller… more
Date: April 1947
Creator: Darsow, John F. & Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of a Thermal Ice-Prevention System for a Cargo Airplane 9: The Temperature of the Wing Leading-Edge Structure as Established in Flight

Description: Report presenting flight measurements of structure temperatures occurring in the wing outer panel of the airplane in order to improve the design of thermal ice-prevention systems. Results indicate that structure temperatures increased almost in direct proportion with an increase in heated-air temperature.
Date: June 1948
Creator: Schlaff, Bernard A. & Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Empirical Equation for the Coefficient of Heat Transfer to a Flat Surface From a Plane Heated-Air Jet Directed Tangentially to the Surface

Description: Note presenting an investigation of the heat transfer to a surface from plane heated-air jets discharged tangentially to the surface to provide heat-transfer relationships required in the design of heated-air jet installations for aircraft windshield fog prevention. Experimental temperature, velocity, and heat-transfer data were obtained by tests in which the initial jet temperature and velocity were varied.
Date: June 1946
Creator: Zerbe, John & Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range With Free-Fall Models

Description: Memorandum presenting an NACA submerged inlet and an NACA series I nose inlet installed in bodies of 12.4 fineness ratio to determine the drag and pressure-recovery characteristics of each body-inlet configuration. The tests were conducted with large-scale free-fall models released at an altitude of 40,000 feet, for mass-flow ratios of about 0.4 and 0.7 over a Mach number range of about 0.70 to 1.10. Results regarding drag and ram-recovery ratios are provided.
Date: June 18, 1951
Creator: Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Drag and Pressure Recovery of a Scoop Inlet in the Transonic Speed Range

Description: "The drag and pressure recovery of a scoop-inlet model have been investigated at transonic speeds by the free-fall testing technique over a Mach number range from about 0.8 to 1.12. Tests were conducted at zero angle of attack, using both rounded and sharp lips at mass-flow ratios from about 0.6 to 0.9. The results indicate that the Mach number of drag divergence of the scoop-inlet model was about the same as that of the basic model without inlets which was tested previously" (p. 1).
Date: December 15, 1952
Creator: Selna, James; Bright, Loren G. & Schlaff, Bernard A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Drag and Pressure Recovery of a Submerged Inlet and a Nose Inlet in the Transonic Flight Range With Free-Fall Models

Description: "The drag and pressure recovery of an NACA submerged-inlet model and an NACA series I nose-inlet model were investigated in the transonic flight range. The tests were conducted over a mass-flow-ratio range of 0.4 to 0.8 and a Mach number range of about 0.8 to 1.10 employing large-scale recoverable free-fall models. The results indicate that the Mach number of drag divergence of the inlet models was about the same as that of a basic model without inlets" (p. 1).
Date: December 28, 1951
Creator: Selna, James & Schlaff, Bernard A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Empirical Equation for the Coefficient of Heat Transfer to a Flat Surface From a Plane Heated-Air Jet Directed Tangentially to the Surface

Description: Note presenting an investigation of the heat transfer to a surface from plane heated-air jets discharged tangentially to the surface was conducted to provide heat-transfer relationships required in the design of heated-air jet installations for aircraft windshield fog prevention. Experimental temperature, velocity, and heat-transfer data were obtained by tests in which the initial jet temperature and velocity were varied.
Date: June 1946
Creator: Zerbe, John & Selna, James
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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