It includes strength analysis and design for uniform materials in the optimization to produce the best possible practical design. Experience has shown this to be an important design factor.
Data calculated include: local flow field thrust and power grading curves, mass flow, mean wake velocity, section lift and drag coefficients, Reynolds number, Mach number, fan diameter, effective pitch, activity factor, efficiency, blade pitch angle, blade angle-of-attack, thrust and power coefficient, fan rpm, gear reduction factor, speed of sound, static thrust, fan chords, blade angles and airfoil coordinates at every desired blade station. Blade strength output includes margin of safety, bending, tensile and compressive stresses, tip deflection and blade weight.
Program input is interactive with on-line definitions for each input. The input calls for starting fan size, engine horsepower and specific fuel consumption data, performance objectives and design constraints or requirements. The program allows the user to input any desired airfoil and optimize pitch distribution, taper or planform shape. Section data may be input at each blade radial station. The program corrects drag and lift for local variation in Reynolds number and Mach number radially. It accounts for user airfoil characteristics by input of upper and lower angle of attack limits for drag divergence variation with Mach number, variation of the zero lift line angle with Mach number and airfoil thickness ratio. To get you started, the Clark-Y and R.A.F.-6 airfoils are built into the program.