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Influence of end plates on lift and flow field of a canard-type control surface at a Mach number of 2.00

Description: "The influence of triangular-shaped end plates on the lift and the flow field of a canard-type control surface mounted on a symmetrical fuselage was investigated in the Lewis 8- by 6-foot supersonic wind tunnel at a Mach number of 2.00, body angle of attack of 2 degrees, and control-surface deflection angles of 3 degrees, 6 degrees, 8 degrees, and 10 degrees. The investigation demonstrated that the addition of end plates to a canard-type control surface increased its lift and rearranged the sin… more
Date: March 23, 1953
Creator: Wise, George A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Force and pressure recovery characteristics at supersonic speeds of a conical spike inlet with a bypass discharging from the top or bottom of the diffuser in an axial direction

Description: Force and pressure-recovery characteristics of a nacelle-type conical-spike inlet with a fixed-area bypass located in the top or bottom of the diffuser are presented for flight Mach numbers of 1.6, 1.8, and 2.0 for angles of attack from 0 degrees to 9 degrees. Top or bottom location of the bypass did not have significant effects on diffuser pressure-recovery, bypass mass-flow ratio, or drag coefficient over the range of angles of attack, flight Mach numbers, and stable engine mass-flow ratios i… more
Date: March 23, 1953
Creator: Allen, J. L. & Beke, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Demand Computer for Project SIR

Description: Abstract: "A description of the demand computer and its functions is given. Methods of testing and adjusting, and gain and response curves for the system and its parts are included."
Date: March 23, 1953
Creator: Raber, R. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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