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activities Administration AERONAUTICS AND SPACE aircraft airplane analysis angle annoyance applications approach assessment Center changes characteristics coefficient composite concept conducted configuration considered continuous contribution deflection delay demands density determined developed difference direct distribution drive edge effects equals equation error evaluation experimental factors fatigue field Figure flap flight flow forebody frequency function given important improvement impulse increased indicators input leading-edge limited load Mach number mean measurements motion NASA NATIONAL AERONAUTICS noise noted obtained occurs operational parameters percent performance pilot presented pressure probe problem PUBLICATIONS range ratio reference Report Research response sample segments shown shows significant simulated Spoiler stress subjects surface TABLE task TECHNICAL techniques temperature thickness tion trailing transport units values variables variation vertical vortex wing wire
Page 29 - No. 12. Sponsoring Agency Name and Address 13. Type of Report and Period Covered 15.
Page 39 - Fatigue is a term used to cover all those determinable changes in the expression of an activity which can be traced to the continuing exercise of that activity under its normal operational conditions, and which can be shown to lead, either immediately or after delay, to deterioration in the expression of that activity, or, more simply, to results within the activity that are not wanted.
Page 13 - Bamberger, EN, et al., Life Adjustment Factors for Ball and Roller Bearings — an Engineering Design Guide, ASME, New York, 1971.
Page 28 - Gillis, Clarence L.; Polhamus, Edward C.; and Gray, Joseph L., Jr.: Charts For Determining Jet-Boundary Corrections for Complete Models In 7- by 10- Foot Closed Rectangular Wind Tunnels.
Page 23 - 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 9 - For sale by the National Technical Information Service. Springfield, Virginia 22161 1 Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA CR-2885 4. Title and Subtitle 5. Report Date "Computers for Real Time Market Survey" Flight Simulation: A July 1977 6.
Page 3 - Polhamus, EC: A Concept of the Vortex Lift of Sharp-Edge Delta Wings Based on a Leading-Edge-Suction Analogy.
Page 5 - ... devices. 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 40 to 50 percent at distances behind the transport model of from about 7 to 27 transport wing spans. 27 spans being the downstream limit of distances used in this investigation Results obtained at about 7 wing spans downstream for two of the spoiler configurations indicate that essentially all the...