## NASA technical note1960 - Aeronautics |

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acceleration aerodynamic airplane altitude Aluminum angle of attack approximately assumed atmosphere calculated characteristics chart coefficient configuration considered constant Copper correction damping decrease deflection derivatives determined Diam diffuser distance disturbance earth effect Enthalpy Entropy entry equation factor feet flight flow force frequency function given ground hardness heat impact inch increased indicated induced initial Langley Lead lift limit loading lunar Mach number material maximum measured method miles moon motion NACA NOTE obtained orbit oscillation percent pilot pitch pivot plane plotted position presented pressure projectile properties range ratio reduced reference respect roll rotating rotor satellite shown in figure shows speed spoiler stability Steel strength surface temperature tests tion trajectories tunnel values variation vehicle velocity wing yield zero

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Page 30 - AMES RESEARCH STAFF : Equations, Tables, and Charts for Compressible Flow. NACA Rep. 1135, 1953. ( Supersedes NACA TN 1428.

Page 22 - Summary of Methods for Calculating Dynamic Lateral Stability and Response and for Estimating Lateral Stability Derivatives.

Page 14 - Both the oscillation and the rolling-flow tests were made at a dynamic pressure of 24.9 pounds per square foot which corresponds to a...

Page 22 - Effects of Wing Position and Fuselage Size on the Low-Speed Static and Rolling Stability Characteristics of a Delta -Wing Model.

Page 9 - 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 29 - NIELSEN, JACK N., GOODWIN, FREDERICK K., and MERSMAN, WILLIAM A., "Three-Dimensional Orbits of Earth Satellites Including Effects of Earth Oblateness and Atmospheric Rotation," NASA Memorandum 12-4-58A, December 1958.

Page 13 - The longitude of a position on the earth's surface is measured by the arc of the equator intercepted between the 'prime meridian and the meridian passing through the place, or by the angle at the pole between those two meridians.

Page 6 - SOME STATIC, OSCILLATORY, AND FREE-BODY TESTS OF BLUNT BODIES AT LOW SUBSONIC SPEEDS, Jacob H.

Page 8 - Styri, Haakon: Fatigue Strength of Ball Bearing Races and HeatTreated 52100 Steel Specimens.

Page 30 - THE AERODYNAMIC DESIGN OF HIGH MACH NUMBER NOZZLES UTILIZING AXISYMMETRIC FLOW WITH .APPLICATION TO A NOZZLE OF SQUARE TEST SECTION, Ivan E.