Lot of 20 NASA Technical Notes D-1780 to D-1799 Apollo, Gemini Era-See Details

Description: Lot of 20 NASA Technical Notes D-1780 to D-1799 Apollo, Gemini Era Research All complete, in great condition! From a library collection, over 1,000 unique NASA Technical Notes Contents of this group: D-1780Apr-63Geometrical Characteristics of Lunar Orbits Established From Earth-Moon TrajectoriesD-1781May-63Effects of Nose Bluntness, Fineness Ratio, Cone Angle, and Model Base on the Static Aerodynamic Characteristics of Blunt Bodies at Mach Numbers of 1.57, 1.80, and 2.16 and Angles of Attsck up to 180°D-1782Apr-63A Simplified Method for Measuring Human Transfer FunctionsD-1783May-63Direct Velocity Measurements in Low-Density Plasma FlowsD-1784May-63An Experimental Investigation of the Effectiveness of Single Aluminum Meteoroid BumpersD-1785Jun-63Investigation of Mechanical Properties and Metalurgical Characteristics of a Metallic Chromium and Magnesium Oxide CompositeD-1786Apr-63Static Aerodynamic Characteristics of a Three-Stage Rocket Vehicle Having Various Fin Configurations at Low Subsonic Mach Numbers and Angles of Attack up to 28°D-1787May-63Helium Concentrations Downstream of a Vent Exhausting Helium at Sonic Velocity into a Supersonic Stream of Air at Mach Numbers of 3.51 and 4.50D-1788May-63Effect of Aerodynamic Heating on the Flutter of Thin Flat-Plate Arrow WingsD-1789Apr-63Aerodynamic Characteristics of Towed Spheres, Conical Rings, and Cones Used as Decelerators at Mach Numbers From 1.57 to 4.65D-1790May-63Heat-Transfer and Pressure Distributions at Mach Numbers of 6.0 and 9.6 Over Two Reentry Configurations For the Five-Stage Scout Vehicle D-1791May-63Tabulated Values of Bond Dissociative Energies, Ionization Potentials, and Electron Affinities For Some Molecules Found in High-Temperature Chemical ReactionsD-1792Jul-63Static Longitudinal Aerodynamic Characteristics of an Elastic Canard-Fuselage Configuration as Measured in Air and in Freon-23 at Mach Numbers up to 0.92D-1793Jun-63Center-Line Pressure Distributions on Two-Dimensional Bodies with Leading-Edge Angles Greater Than That For Shock Detachment at Mach Number 6 and Angles of Attack up to 25°D-1794May-63A Study of Several Factors Affecting the Flutter Characteristics for Two Swept Wings by Piston Theory and by Quasi-Steady Second-Order Theory and Comparion with Experiments D-1795Mar-63A Comparison of Experimental and Theoretical Results For the Compressible Turbulent-Boundary-Layer Skin Friction with Zero Pressure Gradient D-1796Oct-64Longitudinal Stability Characteristics of Low-Aspect-Ratio Wings Having Variations in Leading-Edge and Trailing-Edge ContoursD-1797May-63Moving-Cockpit-Simulator Study of Piloted Entries into the Earth's Atmosphere for a Capsule-Type Vehicle at Parabolic VelocityD-1798May-63Progress Report of the NASA Special Committee on Martials Research For Supersonic TransportsD-1799May-63Some Effects of Simulated Bending and Fourth-Stage Size on Local Pressures and Normal-Force Distributions of a Model of a Scout Configuration at a Mach Number of 3.10

Price: 65 USD

Location: Flint, Michigan

End Time: 2025-01-30T02:48:36.000Z

Shipping Cost: 9.88 USD