Airloads.net

The results which we reach by practical flying experiments will depend most of all upon the shapes which we give to the wings used in experimenting . Therefore , there is probably no more important subject in the technics of flying than that which refers to wing formation . Otto Lilienthal 1896

Comparing Aerodynamic Results With The Following :

NACA Experimental Wind-Tunnel Tests

AeroFoil By Donald L.Reid - Virginia State University - USA

DesignFoil By John Dreese - Ohio State University - USA

JavaFoil By Dr. Martin Hepperle - Braunschweig - Germany

Kevin's Code , By Dr. Kevin D.Jones - Naval Postgraduate School - USA

Pablo By Christian Wauquiez - Royal Institute of Technology - Sweden

XFOIL By Prof. Mark Drela & Harold Youngren - Massachusetts Institute of Technology - USA

AVL By Prof. Mark Drela & Harold Youngren - Massachusetts Institute of Technology - USA

LinAir By Dr. Ilan Kroo At Stanford University And Developed By Donald A.Durston At NASA Ames Research Center - Copyrights By Desktop Aeronautics,Inc - California - USA

MonoPlane Equation Code By Dr. James F.Marchman - Virginia Polytech Institute And State University - USA

Multi Surface Aerodynamic By Dr. Patrick Hanley - Hanley Innovations - USA

Surfaces By Great Owl Publishing Engineering Software

Tornado Code Developed As A Cooperation Between The Royal Institute of Technology (KTH) , University of Bristol , Linköping University And Redhammer Consulting Ldt. - Sweden

USAF DATCOM The United States AirForce Stability And Control Data Compendium - Copy Made By Public Domain Aeronautical Software (PDAS) - California - USA

VLAERO Code Made By AMI Analytical Methods Inc. - USA

XFLR5 By Andre Deperrois

Test Cases : ( Some Tests With Airloads Older Versions )

1 : Infinite Flat Plate

2 : Circular & Elliptical 2D Surfaces

3 : Karman-Trefftz Airfoil

4 : NACA TR No. 824 - March 1945 , 0015 Symmetric Airfoil

5 : NACA TR No. 824 - March 1945 , 2412 Four Series Airfoil

6 : NACA TR No. 537 - May 1935 , 23012 Five Series Airfoil

7 : NACA TR No. 537 - May 1935 , 23112 Reflexed Airfoil

8 : NACA TR No. 537 - May 1935 , 25112 Reflexed Airfoil

9 : NACA TR No. 537 - May 1935 , Wing Number Three

10 : NACA TR No. 537 - May 1935 , Wing Number Seven

11 : NACA TR No. 537 - May 1935 , Wing Number Nine

12 : NACA TN No. 1269 - April 1947 , Wing Number One

13 : NACA TN No. 1269 - April 1947 , Wing Number Two

14 : NACA TN No. 1269 - April 1947 , Wing Number Three

15 : NACA TN No. 1422 - Dec 1947 , Wing Number One

16 : NACA TN No. 1422 - Dec 1947 , Wing Number Two

17 : NACA TN No. 1422 - Dec 1947 , Wing Number Three

18 : Random Wing With 4412 Airfoil Sections , Aspect Ratio = 6

19 : Flat Plate Wing , Aspect Ratio = 10

20 : Flat Plate Wing , Aspect Ratio = 2.352

21 : Complete Aircraft Configurations

22 : Supersonic Air-to-Air Missile At Mach Four

23 : Supersonic Sharp Delta Wing At Mach Six (Airloads older version results)

24 : Supersonic North American XB-70 At Mach 2.4

25 : Supersonic North American XB-70 At Mach 4

26 : Supersonic Arrow wing at mach four , notch ratio = 0.1264

27 : Supersonic Arrow wing at mach three , notch ratio = zero

28 : Supersonic High Aspect Ratio Swept Cambered Wing At Mach 3

29 : Supersonic Sukhoi-37 At Mach 2.5

30 : AIM-7 Short Range Air-to-Air Missile at Mach 4.6

31 : Supersonic Uncambered Rectangular Wing at Mach 2

32 : NASA TN-D-3767 , Vortex Flow Using Leading Suction Analogy