Program AirLoads :
- Using An Advanced Vortex Lattice Method Together With Two Different Surface Distribution Panel Methods And The Classical Thin Airfoil Theory With The Conformal Mapping Analysis , Program Airloads® Analytically And Numerically Solving The Potential Flow About Arbitrary Two And Three Dimensional Lifting And Non-Lifting Surfaces , At Subsonic And Supersonic Flow Fields
- Very Powerful Computational Algorithm For Conceptual And Preliminary Design of Aero Vehicles , Specially Rotor Crafts , Tail-less Aircrafts , Delta Wings , Skewed And Asymmetric Wings , With Almost Any Possible Cross Section
- Program Airloads® Computes The Time Dependent Potential Rise In The Flow Field About Almost Any Shape , By Discretizing The Bounded Surfaces Into Small Rectilinear or Quadrilateral Second/Third/Higher Order Skewed Panels , These Panels Maybe Located on The Actual Surface or on The Mean Cambered Surface or Even on The Chord Plane
- 40 Different Mathematical Model To Solve The Potential Flow About Arbitrary Surfaces
Program Abilities :
- The Program Is Very Flexible To Handle Almost Any Configuration , Like Circles , Ellipses , Spheres , Ellipsoids of Revolution , Rotary Blades , Flat And Cambered Airfoils And Wings
- Any Number of Non-Lifting Surfaces
- Any Number of Wings , Maximum Six Partitions For Each Wing
- Each Partition Has Its Own :
- Span , Root Chord , Tip Chord
- Root Airfoil , Tip Airfoil
- Sweep-back Angle And Sweep Pivot
- Twist Angle
- Dihedral Angle
- Paneling Spacing And Numbering Along Chord Wise And Span Wise
- Trailing Edge Control Surface Configurations ( chord ratio , number of panels , deflection angle , deflection symmetry )
- Program Airloads® Is A Two And Three Dimensional Grid Generator For Different Types of Panel Methods (curved or flat panels on both upper and lower surfaces , curved or flat panels on mean surface , or on the chord plane) , With Four Different Paneling Spacing Schemes In X And Y Directions
- Option To Sweep Back Partitions About Any Sweep Pivot , For Each Partition There Is A Different Sweep Back Angle And A Different Sweep Pivot
- Twist Pivot Is The Same For Each Wing About Any Chord Point , While The Twist Angle May Differ For Each Partition on The Same Wing
- Partitions on The Same Wing May Have Different Dihedral Angles , And Different Chord Wise And Span Wise Paneling
- Program Airloads® Generates Plenty of Airfoils Which Can Be Easily Built And Tested While Inputting The Geometry Data , Choosing The Required Set of Airfoils Allows The Program To Build A Three Dimensional Surfaces For All Lifting Surfaces In The Configuration , But Each Wing Must Have The Same Airfoil Family , For Example, User Can't Use Six-Series Airfoil At The Root And A Modified Reflexed Five Series At The Tip
- Calculating Airfoils Contours At All Span Wise Stations And In Between , With Airfoils Number of Panels Related To The Wing Chord Wise Paneling , Gives High Accurate Slopes of These Airfoils Mean Lines At Each Control Point , Which In Turn Improving The Accuracy of All Proceeding Calculations
- Three Different Aerodynamic Methods For The Construction of The Vortex Lattice , Lattice located on The Chord Plane or Located on The Mean Cambered Surface or Located on The Actual Surface
- Three Methods For The Trailing Vortex Lines Representing The Wake , Extend Them From Each Bound Vortex To Infinity , or From The Bound Vortex To The Panel Trailing Edge Then To Infinity , or From The Bound Vortex To The Partition Trailing Edge And Then To Infinity
- Three Methods For The Trailing Wakes Shape , Rigid Flat Wake Parallel To The X-Axis or Parallel To The Free Stream , Wake Relaxation Technique , Time Marching Procedure
- Each Trailing Vortex Line Divided Into A Number of Straight Vortex Segments , This Number Depends on The Wake Relaxation Factor or on The Time Interval At Which Calculations Are To Be Performed , Also Depends on The Far DownStream Overall Trailing Vortex Extension
- Two Methods For How Far Can We Extend These Wakes , Function of The Reference Span , or Function of The Reference Chord
- Program Airloads® Calculates Complete Dimensional And Non-Dimensional Aerodynamic Forces And Moments , Static And Dynamic Stability And Control Derivatives , In The Wind And Body Axes Systems , Also The Span Load , Span Efficiency , Forces And Moments on Each Panel With The Resultant Normalized Forces , Pressure Distribution , Shear Load Distribution , Bending , Twisting And Torsional Moments Distributions , At Altitudes Up To 25 km
- Induced Drag Calculations By Summing Up The Pressure Forces Due To The Generated Vortices on Each Panel , And Also In The Imaginary Trefftz Plane Far Behind The Configuration Model
- Rate of Change of Forces And Moments With Respect To The Angle of Attack , SideSlip Angle , Angular Velocities , Control Surfaces Deflection
- The Program Automatically Generates An Output File Which Can Be Used As An Input File Again , In Case Users Dont Want To Invoke The Program GUI To Input The Required Geometry Data
- Typical Input File , Output File
- Program Airloads® First Version Oct 2008
