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addition AERONAUTICS AND SPACE afterburning aircraft alloy angle average axial ball blade Center circumferential Cleveland coefficient concentrations considered constant cost design speed determined direction distortion distribution effects efficiency elements emissions energy engine equation field Figure film thickness flight flow fluid fuel given hydrocarbon increase indicated initial inlet less loss Mach maximum mean measured NASA NATIONAL AERONAUTICS Note obtained operating orbital organic outlet parameter percent performance position presented pressure produce PUBLICATIONS radar radial radius range ratio Reduced reference region relative Research rotor screen sector shown in figure shows softening solute SPACE ADMINISTRATION span stage stall station stator studies surface TABLE TECHNICAL temperature tion total pressure trailing transport United velocity waste wing
Page 1 - The four combinations of flight- spoiler segments investigated were effective in reducing the induced rolling moment on the trailing wing model by as much as...
Page 3 - INTRODUCTION The strong vortex wakes generated by large transport aircraft are a potential hazard to smaller aircraft. The National Aeronautics and Space Administration is involved in a program of model tests, flight tests, and theoretical studies to determine the feasibility of reducing this hazard by aerodynamic means.
Page 28 - Urasek, Donald C. ; and Janetzke, David C. : Performance of Tandem -Bladed Transonic Compressor Rotor with Tip Speed of 1375 Feet Per Second.