Airfoil & Wing Aerodynamic Analysis

The aerodynamic performances of airfoil with inlet, ram-air wing and paraglider with payload system can be predicted by the Calculator. The remote program DVM-2 is applied in this case. Thus, this task is solved by our server. For this purpose, fill in forms below (data, your e-mail address and name) and submit. Then e-mail with form will be received by the server, processed and sent with the results back to your e-mail box. We need your e-mail address because these products are e-mail based. If you have concerns about giving out your e-mail address, please read our statement of integrity. The Calculator will run JavaScripts. Be sure your browser supports this language, otherwise install Netscape Navigator (recommended) or Internet Explorer.

If you are interesting to define only the airfoil performances, you have to fill in "Airfoil Geometry" and submit the form. Other data will be ignored.

Data Form

Wing planform:
Canopy planform real area in flight (sq.m)=
Spanwise in flight (m)=
Central chord length (m)=
Relative thickness of airfoil in flight =
Relative curvature of airfoil in flight =
Derivative d(Cy)/d(Attack) =

Suspension lines and flares
Number of suspnension lines
Average length of line =
Diameter of line =
Drag coeff. of suspension line =
Flares area =
Flare drag coefficient =

Payload weight (N)
Payload drag coefficient =
Payload referenced area (sq.m) =

Air density (kg/cub.m)
Reynolds number based on central chord length =

Airfoil Aerodynamic Performances
Fill in the fields in this table and check "Use this table" radio-button if the airfoil performances are known. Data Cx(0), Cy(0) in first row must be included. Other data may be omited and will be predicted by code, but the result in this case can be rough to some extent. If Cx,Cy coefficients are unknown, check "Ignore this table" radio-button and code will predict the airfoil performances in accordance with geometry presented by user in the text field table "Airfoil Geometry" . Input angle of attack in the range [0;20] in ascending order (decrement ~2 recommended) .

___Use this table ___Ignore this table ___

Angle of attack

(in degrees)

Drag coeff.


Lift coeff.



Airfoil Geometry
If you check the radio-button "Ignore table..." above, then airfoil geometry must be assigned in the following text field. The code enables to predict Cx, Cy coefficients in the range of angle of attack between 0 and 20 degrees. The format for each point: [X] [Y] [comments] separarted by space. You should indicate in comment the position of inlet if any. The list containing at least 20 points is recommended for smoothed geometry. If the geometry is very complex, or your browser can't import list of points from other files, you may send the geometry file separately by regular e-mail as a ZIP attachment. The file can be also in DXF, DWG, 3DS and other CAD formats supported/converted by AutoDesk products. The files in graphic formats GIF and JPEG are acceptable as well. Anyway the size of files mailed separately must be limited by 40Kb.

Geometry option: Polyline (broken line) or Smoothed (B-spline)

The result must be sent in the following form (all as a function of angle of attack) (check the boxes):

Drag and lift coefficients: (TABLE)__(GRAPH)
Pressure distribution around upper surface: (TABLE)__(GRAPH)
Pressure distribution around lower surface: (TABLE)__(GRAPH)
Full data file with results (for PostProcessor):

Drag and lift coefficients (TABLE)__(GRAPH)
Lift-to-Drag ratio (TABLE)__(GRAPH)
Lifting force moment coefficient (TABLE)__(GRAPH)
Position of suspension lines (TABLE)__(GRAPH)
Horizontal velocity in flight Vx (TABLE)__(GRAPH)
Vertical velocity in flight Vy (TABLE)__(GRAPH)
Vx/Vy ratio in flight (TABLE)__(GRAPH)
Full data file with results (for PostProcessor):

E-mail form:
Your Name
Your E-mail Address
Add information, suggestion, comment, specific requirements if any. Describe the task if data above are not comprehensive. Indicate the range/list of parameters if serial computing needed.

check appropriate boxes to accept
Airfoil performances prediction = $200
Paraglider performances prediction = $50
( Cx(a),Cy(a) table for airfoil is assigned by user)
Airfoil and Paraglider performances prediction = $250
Test task (default data form). Try it to see how our service works =FREE
Discount for serial computing and optimization = 15%
Pre-Pocessor DVM-2 = $1.500
Post-Processor DVM-2 = FREE
Full featured package DVM-2 = $4.800
The bill will be e-mailed with the results.
Form of payment: wire transfer.

Receipt of your order and timing of work will be confirmed via e-mail

Return to Calculator Main Page