5 Matching Results

Search Results

Results: 1 - 5
open access

Experimental Investigation of a Transonic Axial-Flow-Compressor Rotor Designed for Sonic Inlet Velocity with an Inlet Hub-Tip Radius of 0.35

Description: Memorandum presenting a high-flow sonic-inlet compressor rotor employing double-circular-arc blade sections that was designed and tested in Freon-12. Results regarding overall performance, radial distribution, and blade-element performance are provided.
Date: September 28, 1956
Creator: Boxer, Emanuel & Bernot, Peter T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Investigation of an Axial-Flow Compressor Rotor With a Hub-Tip Ratio of 0.75 and Blades Having NACA A(Sub 2)I(Sub 8b) Mean Lines

Description: Report presenting a blade-element analysis of a compressor rotor with blade sections with NACA A(sub 2)I(Sub 8b) mean lines and 65-series thickness distributions in Freon-12 gas. Results regarding blade loss, angle of attack associated with minimum loss, peak efficiencies, and comparison with other transonic rotors are provided.
Date: September 30, 1957
Creator: Bernot, Peter T. & Savage, Melvyn
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls

Description: Report presenting an investigation to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and all-movable control surfaces. Testing indicated that all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. Some of the configurations tested include body alone, body with 5 degree … more
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls

Description: Report discussing an investigation to determine the aerodynamic characteristics of hypersonic missile configurations with cruciform trailing-edge flaps with all-movable control surfaces. The all-movable controls were found to produce much larger values of trim lift and normal acceleration than the trailing-edge-flap configuration.
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of an axial-flow supersonic compressor having rounded leading-edge blades with an 8-percent mean thickness-chord ratio

Description: Report presenting testing of supersonic compressor blades with rounded leading edges with an 8-percent mean thickness-chord ratio and a solidity of about 2.5 were incorporated in a 16-inch-diameter rotor with and without guide vanes. Results regarding the overall performance, rotor-blade-element performance, and rotor without guide vanes are provided.
Date: December 11, 1953
Creator: Goldberg, Theodore J.; Boxer, Emanuel & Bernot, Peter T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen