Aeronautical+Softwares

= PROPULSION = The best source of propulsion information and software is the [|site by Professor Jack Mattingly]. He is a co-author of the AIAA Aircraft Engine Design book, and the software that goes with it. Various codes are available from him.
 * Gas Turnine Cycle Analysis Programs**
 * **ECAP** - Engine Cycle Analysis Program. This program calculates the variation in performance with design parameters of gas turbine engines (ideal and real) in support of Chapters 5 and 7 in Gordon C. Oates' AIAA textbook [|Aerothermodynamics of Gas Turbine and Rocket Propulsion, Third Edition]. This program was written in QuickBASIC with user-friendly pull-down menus and data fields. It is supplied in executable code with the 1997 edition of Oates' book from AIAA.
 * **EOPP** - Engine Off-Design Performance Program. This program calculates the variation in an engine's off-design performance with changes in flight condition and throttle in support of Chapter 8 in Gordon C. Oates' AIAA textbook [|Aerothermodynamics of Gas Turbine and Rocket Propulsion, Third Edition]. This program was written in QuickBASIC with user-friendly pull-down menus and data fields. It is supplied in executable code with the 1997 edition of Oates' book from AIAA.
 * **OFFX** - Off Design analysis of gas turbine engines (Version 2.2 - May 1996). This program calculates engine performance and supports the first edition of the AIAA textbook //Aircraft Engine Design// (1987). It was written in FORTRAN with user input menus and data. This program along with the **ONX** program in executable codes and the user manual in **Adobe Acrobat** format were included in the first edition, fifth printing of the textbook //Aircraft Engine Design, First Edition//. [|Download ONX and OFFX User Guide]
 * **ONX** - On Design analysis of gas turbine engines (Version 2.2 - May 1996). This program performs engine parametric calculations and supports the first edition of the AIAA textbook //Aircraft Engine Design// (1987). It was written in FORTRAN with user input menus and data. This program along with the **OFFX** program in executable codes and the user manual in **Adobe Acrobat** format were included in the fifth printing of the first edition of the textbook //Aircraft Engine Design, First Edition//. [|Download ONX and OFFX User Guide]
 * **ONX** - On Design analysis of gas turbine engines (Version 5.111 - April 2004 for Windows). This program performs engine parametric calculations and supports the AIAA textbook //Aircraft Engine Design, Second Edition// (2002). [|Program user guide] (1.4MB pdf). Download a prior version free - [|ONX V3.23, Jan 2000] (1.6MB) and copy the self extracting zip file **Onx.exe**. Updated version of this program are now included within the AEDsys system analysis program included with //[|Aircraft Engine Design, Second Edition]//.
 * **PARA** - Parametric Analysis of Gas Turbine Engines (Version 3.1 - Sept 1995). This program calculates the variation in performance with design parameters of gas turbine engines (ideal and real) in support of Chapter 5 and 7 in //Elements of Gas Turbine Propulsion// (1996). This program was written in QuickBASIC with user-friendly pull-down menus and data fields. It is available in executable code with the textbook from McGraw-Hill. (Also available at [|EGTP zip] (635 KB) and copy the self extracting zip file **egtp.exe**)
 * **PARA** - Parametric Analysis of Gas Turbine Engines (Version 4.014 - Feb 2003 for Windows). Download this version free - [|PARA V4.0] (2.4MB) and copy the self extracting zip file **Para.exe**.
 * **PERF** - Performance Analysis of Gas Turbine Engines (Version 3.11 - Sept 1997). This program calculates the variation in an engine's performance with changes in flight condition and throttle in support of Chapter 8 in //Elements of Gas Turbine Propulsion// (1996). This program was written in QuickBASIC with user-friendly pull-down menus and data fields. It is available in executable code with the textbook from McGraw-Hill. (Update available at [|EGTP zip] (635 KB) and copy the self extracting zip file **egtp.exe**)
 * Aircraft/Engine System Analysis**
 * **AEDsys** - Aircraft Engine Design System Analysis Software (Version 3.111 - April 2004 for Windows). This program calculates the performance constraints (wing loading versus thrust loading) and aircraft system performance plots (contour plots) in support of Chapters 2, 5-7 in //Aircraft Engine Design, Second Edition//; and the fuel use and aircraft/engine performance in support of Chapters 3 through 7 in //[|Aircraft Engine Design, Second Edition]//. It is written in Visual Basic 6 with user input menus and data fields (program contains off-design code of OFFX for use in predicting engine performance). [|Program user guide] (4.2MB pdf). Download this prior version free - [|AEDsys V1.26, Jan 2000] (2.7 MB) and copy the self extracting zip file **AEDsys.exe**.
 * Component Preliminary Design**
 * **COMPR** - Multistage Axial Flow Compressor Design (Version 3.11 - Feb 1998). This program calculates the mean-line design of multistage axial flow compressors in support of Chapter 9 in //Elements of Gas Turbine Propulsion// (1996). This program was written in QuickBASIC with user-friendly pull-down menus and data fields. It is available in executable code with the textbook from McGraw-Hill. (Update available at [|EGTP zip] (635 KB) and copy the self extracting zip file **egtp.exe**)
 * **COMPR** - Multistage Axial Flow Compressor Design (Version 5.111 - April 2004 for Windows). This program calculates the mean-line design of multistage axial flow compressors in support of Chapter 8 in //Aircraft Engine Design, Second Edition//. [|Program user guide] (1.7MB pdf). Download a prior version free - [|COMPR V4.3, Jan 2000] (1.7 MB) and copy the self extracting zip file **Compr.exe**.
 * **INLET** - Two-Dimensional Supersonic Inlet Design (Version 3.111 - April 2004 for Windows). [|Program user guide] (1.0MB pdf).
 * **NOZZLE** - Axisymmetric Nozzle Design (Version 3.111 - April 2004 for Windows). [|Program user guide] (1.0MB pdf).
 * **TURBN** - Multistage Axial Flow Turbine Design (Version 3.1 - Sept 1995). This program calculates the mean-line design of multistage axial flow turbines in support of Chapter 9 in //Elements of Gas Turbine Propulsion// (1996). This program was written in QuickBASIC with user-friendly pull-down menus and data fields. It is available in executable code with the textbook from McGraw-Hill. (Update available at [|EGTP zip] (635 KB) and copy the self extracting zip file **egtp.exe**)
 * **TURBN** - Multistage Axial Flow Turbine Design (Version 5.111 - April 2004 for Windows). This program calculates the mean-line design of multistage axial flow turbines in support of Chapter 8 in //Aircraft Engine Design, Second Edition//. [|Program user guide] (1.1MB pdf). Download a prior version free - [|TURBN V4.3, Jan 2000] (1.7 MB) and copy the self extracting zip file **Turbn.exe**.
 * Other**
 * **AFPROP** - Air/Fuel Properties. (Version 2.1 - Sept 1995). This program calculates the thermodynamic properties of air and jet fuels at low pressure in support of the textbook //Elements of Gas Turbine Propulsion// (1996). This program is available in both QuickBASIC source code and executable code with the textbook from McGraw-Hill. (Also available at [|EGTP zip] (635 KB) and copy the self extracting zip file **egtp.exe**)

= Takeoff Distance Calculation = This program computes the takeoff distance, including the balanced field length. The program uses the method of Krenkel and Salzman. Two versions are available. The original FORTRAN program was written by Sean Lynn as an undergraduate research project. After some initial experience, a few improvements to the numerics were made by Pete MacMillin, who felt compelled to convert the code to c. For the test case, there is very little difference between the answers from the two different codes. The input files are also slightly different between the FORTRAN and c verisons. The basic theory is contained in Sean's, final report, which is available as a pdf file.


 * [|Takeoff theory] Sean Lynn's final report
 * [|TAKEOFF2manf.pdf]
 * [|takeoff2.f]
 * [|takeoff2.exe]
 * [|TAKEOFF2.IN] the sample input
 * [|TAKEOFF2.OUT] the sample output
 * [|DC9.IN] a sample DC-9 case
 * [|747.IN] a sample 747 case
 * [|takeoff2.c]
 * [|TAKEOFF2cman.pdf]
 * [|takeoff.in] the sample input
 * [|takeoff.out] the sample output

= Landing Gear Integration in Aircraft Conceptual Design = by Sonny T. Chai and William H. Mason MAD Center Report: MAD 96-09-01, September 1996 Supported by NASA Ames Research Center under Grant NAG-2-919 Multidisciplinary Analysis and Design Center for Advanced Vehicles Virginia Polytechnic Institute and State University Blacksburg, Virginia, 24061-0203 The design of the landing gear is one of the more fundamental aspects of aircraft design. The design and integration process encompasses numerous engineering disciplines, e.g., structures, weights, runway design and economics, and has become extremely sophisticated in the last few decades. Although the design process is well-documented, it is not available in an integrated design methodology that can be used within an automated environment. The process remains a key responsibility of the configuration designer and is largely experience-based and graphically-oriented. However, as industry and government try to incorporate multidisciplinary design optimization (MDO) methods in the conceptual design phase, the need for a more systematic procedure has become apparent. The MDO-capable design methodology described in this report is focused on providing the conceptual designer with tools to help automate the disciplinary analyses, i.e., geometry, kinematics, flotation, and weight. The methods were developed by studying available documented design procedures and analyses together with an industrial survey. We then used our approach to study advanced large subsonic transports. The resulting methodology is available in the form of codes that can be used in existing MDO programs. This report is available electronically as a series of Adobe Acrobat files. The Adobe Acrobat reader is widely available for free, and is in theory platform independent. The report is provided in a format assuming it will be copied in a front and back style (meaning that there a few blank pages to start key sections on add numbered pages). The [|front part of the report] is available as a single pdf file (33k) containing: (Revised April 1, 1997) The body and appendices are avialble individually: Landing gear configuration selection flotation analysis Constraint violations determination Landing gear weight estimation This work would not have been possible without the support of NASA Ames Research Center, under grant NAG-2-919. Paul Gelhausen and Shahab Hassan served as technical monitors. At Virginia Tech Dr. Eric R. Johnson assisted with the analysis supporting the weight estimation methodology and Dr. Antonio A. Trani helped us develop the pavement thickness requirements analysis. We also were helped by a number of other individuals, including Mr. Bill Perrella and Mr. John Rice at the Federal Aviation Administration, Mr. Edward Gervais, Mr. Jerry Kileer, Mr. Bob Nielson, Mr. Dave Nielson, Mr. Scott Perkins, and Mr. John Potter at Boeing Commercial Aircraft Group, Mr. Al Kernik at McDonnell Douglas, Mr. Gene Stuczynski at Cleveland Pneumatic, Mr. Bill Luce at Menasco Aerosystems, Mr. Derek Duxbury at British Aerospace, Mr. Ron Olds, Mr. Dean Peters, and Mr. Paul Snyder at B.F. Goodrich, Mr. Joe Pacuit at the Tire and Rim Association, Inc., Mr. Richard Vandame of the SAE A-5 Committee, Mr. James Gallivan at United Airlines, and Mr. Steve Lydon at Northwest Airlines. We appreciate their assistance and valuable input during the initial industry survey. Last but not least, we acknowledge Mr. Nathan Kirschbaum at Virginia Tech for his insight into landing gear design considerations at the aircraft conceptual design stage.
 * Abstract**
 * Electronic Version**
 * Report Title Page
 * Abstract
 * Acknowledgments
 * Table of Contents
 * List of Figures
 * List of Tables
 * Nomenclature
 * Chapter 1: [|Introduction] (pdf, 33k)
 * Chapter 2: [|Aircraft Center of Gravity] (pdf, 33k) (Revised April 1, 1997)
 * Chapter 3: [|Landing Gear Concept Selection] (pdf, 116k)
 * Chapter 4: [|Tires, Wheels, and Brakes] (pdf, 1400k) (Revised April 1, 1997)
 * Chapter 5: [|Shock Absorber Design] (pdf, 710k) (Revised April 1, 1997)
 * Chapter 6: [|Kinematics] (pdf, 149k)
 * Chapter 7: [|Aircraft Flotation Analysis] (pdf, 83k) (Revised April 1, 1997)
 * Chapter 8: [|Weight Estimation] (pdf, 990k) (Revised April 1, 1997)
 * Chapter 9: [|Analysis Package] (pdf, 33k)
 * Chapter 10: [|Parametric Studies] (pdf, 66k)
 * Chapter 11: [|Costs] (pdf, 17k)
 * Chapter 12: [|Future Considerations] (pdf, 17k)
 * Chapter 13: [|Conclusions] (pdf, 17k)
 * [|References] (pdf, 17k)
 * Appendix A: [|Industry Survey] (pdf, 33k)
 * Appendix B: [|Structural Analysis] (pdf, 33k)
 * Appendix C: [|Bibliography] (pdf, 33k)
 * Appendix D: [|Aircraft Tire Database] (updated Sept. 24, 1997, pdf: 18k)
 * Appendix E: [|Analysis Package User's Manual] (pdf, 33k)
 * The Software: Codes and data sets**
 * config.f
 * [|TIRE.DAT] a required data file for config
 * [|747CONF.INP] sample input
 * 747CONF.OUT sample output
 * pave.f
 * [|PAVECOEF.DAT] a required data file for pave
 * [|747PAVE.INP] sample input
 * 747PAVE.OUT sample output
 * limit.f
 * [|747LIMI.INP] sample input
 * 747LIMI.OUT sample output
 * gearwei.f
 * [|747WEIG.INP] sample input
 * 747WEIG.OUT sample output
 * Acknowledgments**

Software for Aerodynamics and Aircraft Design (W.H. Mason, Virginia Tech)
This page contains various programs that may prove useful to aerodynamics and design class students. These are mostly old-fashioned codes without graphical user interfaces. In fact this was originally all FORTRAN source code. However, I’ve recently started adding executables since the FORTRAN source files typically can’t be used by current undergraduates. In addition, some methods are given as MATLAB m-files. Another source of classic aerodynamics codes is the CD sold by Ralph Carmichael, [|Public Domain Aeronautical Software (PDAS)]. **Important Note:** Many of these programs require a text file as input. **DO NOT** embed tabs in these files. **ALSO**, the location of the input on each line is critical. The input instructions are often given as “cards”, from the days when the text files were physically a deck of computer cards. The spacing definitions use FORTRAN terminalogy. Do yourself a favor and learn what this means. For example, F10 means a real number (with a decimal point) taking 10 spaces. Study the sample input files for examples of how this works (in fact, ALWAYS run the sample case before doing anything else with these codes). For pointers on running codes, read the chapter from my Applied Computational Aerodynamics notes, [|Computers, Codes, and Engineering] (a pdf file). In some cases I have now added links to sites located elsewhere, where key codes are available. Other useful online Java-based programs are available at [|www.engapplets.vt.edu]. Comments or questions? Contact me at whmason@vt.edu. Last modified: March 27, 2007. 

Aerocal Pak #1
This software is a BASIC program that implements the old Aerocal Pak #1, //Basic Aerodynamic Relations//. It has the NACA 1135 tables, Prandtl-Meyer angle and inverse, properties of oblique shocks, the Rayleigh/Fanno line table and the 1976 standard atmosphere. Originally written for a programmable calculator, the code is in QuickBASIC, and runs as is on a Mac with QuickBASIC. A one line change is required to run it on an IBM type PC. The file is standard ascii text.

[|Back to the code menu]
 * [|Aerocal Pak #1]

stand alone NACA 1135
These codes compute the compressible flow functions given in NACA 1135, plus a few more useful relations. These are executables that replace the NACA 1135 portions of Aerocal Pak#1 above, which doesn't run on many computers anymore.

[|Back to the code menu]
 * [|NACA1135.sit] The Macintosh version (stuffed)
 * [|NACA1135.exe] The PC version

Airfoil generation: NACA 4&5 Series
This is an interactive FORTRAN program that allows the user to construct airfoils using the NACA 4 digit or modified 4 digit airfoil thickness distributions and the NACA 4 digit, 5 digit or 6- and 6A series camber lines. A variety of output options are available on the screen. It can also create a file for use as input to airfoil analysis programs. This file is in the so-called "Jameson format". The file is standard ascii text. It should run using any FORTRAN compiler.The theoretical description of the equations used is available as a pdf file which is actually an Appendix to my Applied Computational Aerodynamics Notes.

[|Back to the code menu]
 * [|foilgen.f]
 * [|foilgen.exe]
 * [|Geometry for Aerodynamicists(pdf)]

Airfoil generation: NACA 6&6A Series
This is a FORTRAN program that allows the user to obtain (approximately) the NACA 6 digit or 6A digit airfoils. The program was written at NASA by Cuyler Brooks and Charles Ladson. It appears to be considered to be in the public domain. The file is standard ascii text. It should run using any FORTRAN compiler. The theoretical description of the equations for the camber lines is available as a pdf file which is actually an Appendix to my Applied Computational Aerodynamics Notes. The thickness distribution of these airfoils is not described by a single equation.

[|Back to the code menu]
 * [|LADSON Manual] (pdf)
 * [|LADSONpc.f]
 * [|LADSONpc.exe]
 * [|LADSON.inp]
 * [|LADSON.out]
 * [|Geometry for Aerodynamicists(pdf)]

Planform Analysis
This software includes a BASIC program that implements the old Aerocal Pak #2, //Basic Geometry for Aerodynamics//. I put it up for the little planform and wing analysis programs, which I find still find useful, although today it should be on a spreadsheet. It also generates the shapes for several of the classic bodies of revolution, and has the BASIC (original) version of the FORTRAN program FOILGEN given above for the NACA airfoils. Originally written for a programmable calculator, and then translated to Applesoft, the code is in QuickBASIC, and runs as is on a Mac with QuickBASIC. A one line change is required to run it on an IBM type PC. The file is standard ascii text. The theoretical description is available as a pdf file which is actually an Appendix to my Applied Computational Aerodynamics Notes. An executable of a FORTRAN program in also posted here, together with the manual, sample input and sample output.

[|Back to the code menu]
 * [|Aerocal Pak #2] A BASIC Program
 * [|WingPlanAnal.f] A FORTAN source file for the planform analysis portion of Pak #2.
 * [|WingPlanAnal.exe] An Executable
 * [|WingPlanAnal.pdf] The manual for WingPlanAnal
 * [|B2Plan.inp] A sample input
 * [|B2Plan.out] A sample output

Nicolai's sizing program(s)
I've included four files here. They implement Nicolai's aircraft sizing algorithm in QuickBASIC and more recently, REALbasic. Acsize, provides the size, while the second code, acsweep, covers a range of takeoff gross weights, showing the empty weight required and available. They should run on either Mac or IBM type PCs. In the QuickBASIC versions, data values are set in the program, with the hope that the users will look at the code and see what is going on. The files are standard ascii text. The REALbasic programs are executables for both the Mac and PC. The only modification to Nicolai's notation is a supersonic mission leg.

[|Back to the code menu]
 * [|acsize.QB] The QuickBASIC listing.
 * [|acsweep.QB]
 * [|ACsize.exe] A PC code
 * [|ACsizeMac.sit] A Mac code
 * A similar and likely better code is available from [|Dan Raymer's web site.]

Simple Lifting Line Theory
This is an interactive FORTRAN program that solves the classical Prandtl lifting line theory using the monoplane equation. The file is standard ascii text. It should run using any FORTRAN compiler.

[|Back to the code menu]
 * [|llt.f] The source code.
 * [|llt.exe] An executable for PCs.

Standard atmosphere routines
Originally a FORTRAN subroutine (actually TI-59 and then Applesoft), a MATLAB file is also provided. stdatmtest.m is the driving script file for the MATLAB function file. The subroutine can be used in other programs. It is the same routine used in Pak #1 above. The units are listed in the subroutine header. A sample main program is included to illustrate the use of the program, and it should run using any FORTRAN compiler, or in MATLAB. Note that the MATLAB version was originally converted from FORTRAN by Paul Buller.

The following web-based standard atmosphere calculators have been suggested by students: [|Back to the code menu]
 * [|stdatm.f]
 * [|stdatmf.m]
 * [|stdatmtest.m]
 * [|Digital Dutch]
 * [|Desktop Aeronautics Calculator] from Ilan Kroo’s company
 * [|Tom Gally’s calculator] from Embry Riddle in Prescott, AZ
 * [|AerospaceWeb]
 * [|ConvertIt Calculator]

Skin Friction/Form Factor Drag estimation
This program can be used to estimate the basic friction drag of an airplane. It is from Mason's Applied Computational Aerodynamics Class, and the acrobat manual is App. D.5 of the class notes. It should run using any FORTRAN compiler. Along with the manual and code, a sample input and the resulting sample output are provided. In November of 2002 an executable version has been added.

We also have a Matlab version from Paul Buller from 1998. [|Back to the code menu]
 * [|friction.f] The source code
 * [|friction.exe] The executable
 * [|FRICTman.pdf]
 * [|F15frict.inp]
 * [|F15frict.out]
 * [|friction.m] The main program
 * [|finput.m] The input routine
 * [|lamcf.m] The laminar skin friction routine
 * [|turbcf.m] The turbulent skin friction routine
 * [|stdatm.m] The standard atmosphere

Induced Drag for a single planar wing
Computation of the induced drag of a single planar surface given the spanload distribution. You get a value of the span //e// as output. The coefficients of the assumed Fourier Series are computed using a Fast Fourier Transform. The program was written by Dave Ives, and used in numerous programs developed for the government by Grumman.

[|Back to the code menu]
 * [|LIDRAG Manual] (pdf)
 * [|lidrag.f]
 * [|lidrag.exe]
 * [|lidragB2.inp]
 * [|lidrag.out]

Induced Drag for nonplanar lifting systems
This program can be used to find the induced drag of a system of nonplanar lifting elements. It was written by Joel Grasmeyer. It has both design and analysis capabilities. This means that you either find the spanload required to obtain the minimum induced drag, or you can input a spanload and find the induced drag. The program also prints out the span efficiency factor //e//. This program does not give you the twist and camber required to generate the spanloads. Three FORTRAN programs are required and must be linked to run the program.

[|Back to the code menu]
 * [|idrag.f]
 * [|idragin.f]
 * [|math77.f]
 * [|idrag.exe]
 * [|idragman.pdf] The program manual
 * [|dsample.in] A winglet design example input file
 * [|dsample.idrag] A winglet design example output file
 * [|asample1.in] An analysis example input file (linear load distribution)
 * [|asample1.idrag] An analysis example output file
 * [|asample2.in] An analysis example input file (elliptic load distribution)
 * [|asample2.idrag] An analysis example output file

Induced Drag for simple nonplanar lifting systems, with camber line design
John Lamar's design program, modified to find the span //e// for two nonplanar lifting surfaces given the spanload on each surface. This is a more capable version of LIDRAG. This code also finds the wing camber and twist required to obtain this spanload at subsonic speeds. The code will also do an optimization analysis, finding the minimum trimmed drag and spanload required to achieve it.

[|Back to the code menu]
 * [|LAMDES Manual] (pdf)
 * [|LamDes2.f]
 * [|LamDes2.exe]
 * [|LamDes.inp]
 * [|LamDes2.out]

Minimum drag and area distribution
MinDrag computes the minimum value of the supersonic wave drag, and the area distribution required to attain this value for a given length, XL, volume, nose area [Snose] and base area [Sbase], and with another area specified at a given location along the body [XSgiven, Sgiven]. It uses the formulas published by W.T. Lord and E. Eminton in “Slender Bodies of Minimum Wave Drag,” //Journal of the Aeronautical Sciences//, August, 1954, pages 569-570.

[|Back to the code menu]
 * [|MinDrag.exe]

Harris Wave Drag computation
(manual and data sets only) AWAVE is a version of the Harris Wave Drag code. We have it on the design lab PCs for supersonic aerodynamic design. However, it is not ours to distribute openly. We have put the manual (essentially a description of the Craiden geometry data set), and a sample input and output here.

[|Back to the code menu]
 * [|awave.man] This is the user's manual.
 * [|awaveFileMake.m] A Matlab script file to help make the input file and make sure that the numbers are in the correct columns. The directions on use are contained as comments in the script. Todd Lowe wrote this script for us (version of 2/7/06).
 * [|AWAVEIN.DAT] This is the sample input file.
 * [|AWAVEOUT.DAT] This is the sample output to check your results.

Control Power Assessment
This is a collection of codes that may be useful in aircraft conceptual design. There are two main components, a vortex lattice code to provide at least a rough estimate of the stability and control derivatives, and a spreadsheet to evaluate a design using specified aircraft characteristics. We also have codes that implement the methods of NASA TP 2907 to find the best way to trim the aircraft when you have multiple possibilities. This includes three surfaces, and two surfaces with thrust vectoring.

For the executable of JKayVLM, use these files: The rest of the material is available below:
 * [|VPI-Aero-200.pdf] (the complete report, including the user's manuals for the codes)
 * [|JKayVLM.f] This is the original "small" code. It might fit on a PC.
 * [|JKaydblp.f] This is the double precision version with more panels.
 * [|JKsamp.inp] This is the sample input file
 * [|JKlata.tst] This is the sample input file for the lateral geometry
 * [|JKlonga.tst] This is the sample input file for the longitudinal geometry
 * [|JKsampoutref] This is the sample output to check your results.
 * [|JKayVLM.exe] This is the executable
 * [|f18samp.inp] This is the sample input file
 * [|f18lata.tst] This is the sample input file for the lateral geometry
 * [|f18longa.tst] This is the sample input file for the longitudinal geometry
 * [|f18samp.out] This is the sample output to check your results.

[|Back to the code menu]
 * [|CPRCheck.sit] CPRCheck (the spreadsheet in Lotus 1-2-3 format, in Stuffit format from a Macintosh)
 * [|VPINASACPC.sit] VPI-NASA-CPC (the spreadsheet in EXCEL format and improved by Marty Waszak at NASA Langley, in Stuffit format from a Macintosh.)
 * [|VTnascpc.zip] VPI-NASA-CPC (the spreadsheet in EXCEL format and improved by Marty Waszak at NASA Langley, zipped so that an IBM can download and unzip. It is the same file format from a Macintosh as the .sit file above. EXCEL on IBM should be able to import the file - let me know if there is a problem.)
 * [|fltcond.f] A program to establish various flight conditions to assess the configuration.
 * [|FLTcondSetup.sit] This is a spreadsheet in Lotus 1-2-3 format, in Stuffit format from a Macintosh, to setup the input for the fltcond.f code.
 * [|trim3s.f] (FORTRAN program implementing NASA TP 2907, the version for 3 surfaces)
 * [|3SURFACE.DAT] (input file that reproduces the case in the manual)
 * [|trimTV.f] (FORTRAN program implementing NASA TP 2907, the version for 2 surfaces and thrust vectoring)
 * [|2SURFACE.DAT] (input file that reproduces the case in the manual)

Lateral/Directional estimates and Engine Out
These are codes that can be used to estimate some of the key lateral directional analysis, including stability and control derivatives for use in estimating aircraft characteristics. LDstab is basically an implementation of the DATCOM method, with adjustments to match published B747 data. It should be used in place of lateral-directional estimates from Jacob Kay's code given above, which are on shakey theoretical grounds. This code was developed by Joel Grasmeyer for the truss-braced wing project. The report covers an engine out analysis, but the program doesn't provides the complete analysis. Use VMCA below to do the engine out analysis.

[|Back to the code menu]
 * [|LDstabdoc.pdf] This is the report describing the methods, including the user's manual
 * [|LDstab.f] This is the FORTRAN source.
 * [|LDstab.exe] The executable.
 * [|747LDs.in] This is the sample input file.
 * [|747LDs.out] This is the sample output to check your results.

DigitalDATCOM stability and control estimation
(sample input files only) Digital DATCOM is a code that can be used to estimate stability and control derivatives. It is on our design lab PCs. It is an industrial strength code that has a non-trivial learning curve. However, it has the capability to estimate stability and control characteristics at supersonic speeds. This information is not available in Roskam's volumes, so we needed to add it to our computing library.

[|Back to the code menu]
 * [|DATCOM.IN] This is the sample input file.
 * [|DATCOM.OUT] This is the sample output to check your results.



[|Back to the code menu]
 * [|VMCAUserMan.pdf] This is the manual.
 * [|VMCAv1.m] This is the m-file.

Vortex lattice design to get a 2D camber line for a given chordload
The camber line required to produce a specified chord load distribution is computed using the quasi-vortex lattice method by Prof. Lan of the University of Kansas. The method is valid for two dimensional incompressible flow, and is an original (and very simple) program. Thanks to Tom Zeiller for improvements and bug fixes.

[|Back to the code menu]
 * [|DESCAM Manual] (pdf)
 * [|descam.f]
 * [|descam.exe]
 * [|descam.inp]

Vortex lattice analysis and design: VLMpc
John Lamar's two surface vortex lattice program, developed at NASA Langley. The program treats two lifting surfaces using up to 200 panels. Vortex flows are estimated using the leading edge suction analogy. This program was typed in from the NASA TN D, which contained the listing, by students in Applied Computational Aerodynamics nearly 10 years ago. John Lamar didn't have a copy of the code anymore. It has been modified to run in WATFOR, and to produce 80 column output. Now it runs in Compaq Visual Fortran. In November 2002 an executable has been added. The source now includes PC directory code specific to PCs.

[|Back to the code menu]
 * [|VLMpc Manual] (pdf) Note: this code has many check cases
 * [|VLMpcv3.f] The source code
 * [|VLMpc.exe] The executable
 * [|vlm.dat]
 * [|vlm.out]
 * [|vlm2.dat]
 * [|vlm2.out]
 * [|B767.dat]
 * [|B767.out]
 * [|YF23.inp]
 * [|YF23.out]
 * [|YF23.in2]
 * [|YF23.out2]

Vortex lattice analysis and design: VLM 4.997 manual
VLM 4.997 is a NASA Langley Vortex Lattice Program which can handle four planforms and up to 400 panels. It is an extension and improvement of the two surface code discussed above. This is an Acrobat Manual only. If you want the code you need to contact NASA Langley. Our version is available for student use in the design lab.

[|Back to the code menu]
 * [|VLM 4.997 Manual]
 * [|A7wing.inp] An A-7 with a different wing, wing alone case input
 * [|A7wing.out] the output for this input
 * [|A7wingfus.inp] An A-7 with a different wing, wing-fuselage case
 * [|A7wingfus.out] the output for this input
 * [|A7full.inp] An A-7 with a different wing, wing-fuselage-tail case
 * [|A7full.out] the output for this input

Vortex lattice analysis code in MATLAB: Tornado
Tornado is a Vortex Lattice Program, written in MATLAB. It comes from KTH, the Royal Institute of Technology, in Stockholm, Sweden. Tomas Melin wrote the program, and Professor Arthur Rizzi was his advisor. It is a very flexible program, and can handle a wide range of geometries. Also, it is still being developed, so check the site for updated versions.

[|Back to the code menu]
 * [|Tornado] The location for the code and related manuals.

An extended vortex lattice code from Prof. Drela at MIT and Harold Youngren: AVL
AVLis a very general Vortex Lattice Program. It comes from MIT, and is by the author of the widely used XFOIL airfoil analysis and design code. It is a very flexible program, and can handle a wide range of geometries.

[|Back to the code menu]
 * [|AVL] The location for the code and related manuals.

Subsonic Airfoil Analysis and Design: XFOIL 6.9
XFOIL is an airfoil analysis and design program from Prof. Mark Drela at MIT. It is for essentially incompressible single element airfoils. However, it includes viscous effects, and can be used in an inverse mode, where the pressure distribution is input and the required geometry found. It runs on workstations and win32 PC systems. Some very good airfoil work has been done by design class students with this code.

[|Back to the code menu]
 * [|Xfoil] The location for the code, which is available under the GNU licensing rules, and related manuals and discussion groups.
 * Some [|notes by Tim Miller] on using XFOIL
 * Some more [|notes by Tim Miller] on using XFOIL
 * A sample airfoil, [|clarky.dat]demonstrating the format for inputting coordinates into XFOIL (Tim Miller attributes this data file to JD Jacob at the University of Kentucky)

Subsonic Airfoil Analysis and Design: Pablo
Pablo is a subsonic airfoil analysis and design program. It comes from KTH, the Royal Institute of Technology, in Stockholm, Sweden. Christian Wauquiez wrote the program, and Professor Arthur Rizzi was his advisor. Pablo stands for "Potential flow around Airfoils with Boundary Layer coupled One-way". It is a MATLAB code, so you need to have MATLAB to run it. Eventually, this url will go away, and when it does, Prof. Rizzi has given us permission to put this up on our site at Virginia Tech.

[|Back to the code menu]
 * [|pablo] The location for the code and related manuals.



[|Back to the code menu]
 * [|JavaFoil] The location for the code and related manuals.

Transonic airfoil analysis: TSFOIL2
TSFOIL2 provides a finite difference solution of the transonic small disturbance equation. It will run on my Mac with no problem. The source code is provided as standard ascii text. The code was written by Earll Murman and co-workers, and includes wind tunnel wall effects. It originated at NASA Ames. It’s very old, but appears to be in the public domain. The listing was included in a NASA CR which is referenced in the mini-manual provided here as a pdf file. The NASA CR (3064) is also now available as a pdf file from the NASA Technical Reports Server.

[|Back to the code menu]
 * [|TSFOIL2 Manual] (pdf)
 * [|tsfoil2.f] The source code.
 * [|tsfoil2.exe] The executable.
 * [|bicon.inp] Sample input for a biconvex airfoil
 * [|bicon.out] Sample output for the biconvex airfoil input
 * [|n2412.inp] Sample input for an NACA 2412 airfoil
 * [|n2412.out] Sample output for the NACA 2412 airfoil
 * [|N0012.inp] Sample input for an NACA 0012 airfoil
 * [|N0012.out] Sample output for the NACA 0012 airfoil
 * [|SC20610.inp] Sample input for a NASA SC(2)-0610 airfoil
 * [|SC20610.out] Sample output for the NASA SC(2)-0610 airfoil

Supersonic aerodynamics of arrow wings
arrow is a code to compute the linear theory lift curve slope, aerodynamic center and drag due to lift of arrow wings at supersonic speed.


 * [|arrow.f] The source code.
 * [|arrow.exe] The PC executable.

= Software Review =

From the Virginia Tech Aircraft Design web pages
This page originated from a paper given at the ASEE Annual Conference, Sunday, June 25, 1995, Anaheim, CA (Gary Slater, session chairman: Software and Multimedia). It has been updated for design class use. Every attempt has been made to be accurate. Please let us know of address changes, typos, and errors.

We also have some design-oriented software available for download. See [|Downloadable Software w/Manuals]
 * [|Aircraft Design and Sizing]
 * [|Geometry]
 * [|Aircraft Performance/Mission Analysis]
 * [|Aerodynamics]
 * [|Propulsion]
 * [|Stability and Control]
 * [|Optimization]
 * [|Other Sources of Programs]