DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click
HERE to register or log in.
Accession Number:
AD0837724
Title:
OPTIMUM AIRFOILS AT MODERATE SUPERSONIC SPEEDS. PART 5. MINIMUM DRAG, INCLUDING BASE DRAG,
Corporate Author:
RICE UNIV HOUSTON TX AERO-ASTRONAUTICS GROUP
Report Date:
1968-01-01
Abstract:
Minimum drag airfoils at moderate supersonic speeds are determined using Busemanns second-order theory for the forebody drag and Chapmans experimental results for the base drag. Two cases are investigated under the assumption that the length is prescribed a given thickness and b given enclosed area. For given thickness, the minimum drag airfoil is a diamond shape with or without a blunt trailing edge depending on the prescribed thickness ratio. For turbulent flow and given Mach number and Reynolds number, two critical values of the thickness ratio exist. For given enclosed area, the minimum drag airfoil is biconvex with or without a blunt trailing edge depending on the enclosed area ratio. For turbulent flow and given Mach number and Reynolds number, a critical value of the enclosed area exists. In both cases, maximum thickness occurs between midchord and the trailing edge. Author
Pages:
0031
Contract Number:
AF-AFOSR-828-67
File Size:
0.00MB
