Author: Willis H. BraunPublisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
Turbulent Boundary Layer on a Yawed Cone in a Supersonic Stream
Author: Willis H. BraunPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
The momentum integral equations are derived for the boundary layer on an arbitrary curved surface, using a streamline coordinate system. Computations of the turbulent boundary layer on a slightly yawed cone are made for a Prandtl number of 0.729, wall to free-stream temperature ratios of 1/2, 1, and 2, and Mach numbers from 1 to 4. Deflection of the fluid in the boundary layer from outer stream direction, local friction coefficient, displacement surface, lift coefficient, and pitching-moment coefficient are presented.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1216
Book Description
Technical Note
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 372
Book Description
Charts and Approximate Formulas for the Estimation of Aeroelastic Effects on the Lateral Control of Swept and Unswept Wings
Author: Almer D. CrimPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 344
Book Description
Investigation of Statistical Nature of Fatigue Properties
Author: E. EpremianPublisher:
ISBN:
Category : Iron
Languages : en
Pages : 746
Book Description
Extensive fatigue tests were made on annealed Armco iron and plain carbon and alloy steels heat-treated to different strengths and microstructures. Statistics of fatigue-fracture curves and endurance limits were determined from the experimental data obtained and, for various other materials, from a survey of literature. The results were analyzed to show the relative effects of various metallurgical factors on the statistical nature of fatigue properties. Other phases of the problem studied include: dependence of statistical variation in fatigue life on stress level in the fracture range, statistics for location of crack initiation, size effect, understressing effect, and the form and method of plotting the S-N diagram.
Applied Mechanics Reviews
Author: A Selected Listing of NASA Scientific and Technical Reports for ...
Author: Index of NACA Technical Publications
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 274
Book Description
Calorimetric Determination of Constant-pressure Specific Heats of Carbon Dioxide at Elevated Pressures and Temperatures
Author: Virgil E. SchrockPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 678
Book Description
The constant-pressure specific heat of carbon dioxide has been measured over the range of temperatures and pressures from ambient condtions to 1000 pounds per square inch gage and 1000 degrees F using a steady-flow calorimeter operated on an open cycle. It appears that the apparatus as used in this determination will yield values with a probable error of 0.5 percent at the highest temperature level considered. The results of these tests check the widely accepted spectroscopic data within 1 percent. The values at elevated pressure are in reasonable agreement with those derived from the zero-pressure spectroscopic values and the application of the Beattie-Bridgeman equation of state. Only very limited calorimetric data are available in the literature, but substantial agreement exists with those considered reliable.
Approximations for the Thermodynamic and Transport Properties of High-temperature Air
Author: C. Frederick HansenPublisher:
ISBN:
Category : Air
Languages : en
Pages : 724
Book Description
The thermodynamic and transport prorerties of high-temperature air are found in closed form starting from approximate partition functions for the major components in air and neglecting all minor components. The compressibility, energy, entropy, the specific heats, the speed of sound, the coefficients of viscosity and of thermal conductivity, and the Prandtl numbers for air are tabulated from 500 degrees to 15,000 degrees K over a range of pressure from 0.0001 to 100 atmospheres. The enthalpy of air and the mol fractions of the major components of air can easily be found from the tabulated values for compressibility and energy. It is predicted that the Prandtl number for fully ionized air will become small compared to unity, the order of 0.01, and this implies that boundary layers in such flow will be very transparent to heat flux.