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Comparing Aerodynamic Results With The Following :

 

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

 

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