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Feb 1

General question: .lod data structure OpenVSP 3.47

Hello, I was checking out the latest VSP3.47 output files and I noticed there is no more .fem file

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General question: .lod data structure OpenVSP 3.47

Hello, I was checking out the latest VSP3.47 output files and I noticed there is no more .fem file

Feb 1

Rob McDonald, Mike Novikov3

Feb 1

Adjoint driven optimization in VSPAERO

Rob, sorry to bother you with the optimization. I checked your file, and it works with version 3.47.0

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Adjoint driven optimization in VSPAERO

Rob, sorry to bother you with the optimization. I checked your file, and it works with version 3.47.0

Feb 1

Violet Philip, Rob McDonald3

Jan 30

Control derivative interpretation

Thank you, Rob for the reply. Violet On Sat, 31 Jan 2026, 01:31 Rob McDonald, <rob.a.mcdonald@

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Control derivative interpretation

Thank you, Rob for the reply. Violet On Sat, 31 Jan 2026, 01:31 Rob McDonald, <rob.a.mcdonald@

Jan 30

Jules Galzin, … Rob McDonald3

Jan 30

Applying different densities to a fuselage

The MassProp calculation in OpenVSP does not use SubSurfaces. However, version 3.45.2 will report

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Applying different densities to a fuselage

The MassProp calculation in OpenVSP does not use SubSurfaces. However, version 3.45.2 will report

Jan 30

Toshio Otaguro, Rob McDonald13

Jan 30

Very tiny fonts in the VSPAERO panel

Many thanks, Rob. I hope you sleep well. 2026年1月30日金曜日 11:35:52 UTC+9 Rob McDonald: OK, I'll try

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Very tiny fonts in the VSPAERO panel

Many thanks, Rob. I hope you sleep well. 2026年1月30日金曜日 11:35:52 UTC+9 Rob McDonald: OK, I'll try

Jan 30

nate carr, … Brandon Litherland4

Jan 29

Changing wing span in .vsp3 file

Hi Rob and Brandon, Thanks, this helps a lot. I'll stop editing the .vsp3 directly and use the .

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Changing wing span in .vsp3 file

Hi Rob and Brandon, Thanks, this helps a lot. I'll stop editing the .vsp3 directly and use the .

Jan 29

Simon Boudoux, Rob McDonald2

Jan 28

Aerodynamic Derivatives wrt to u,v,w

This is normal flight dynamics process. Assuming that you would decompose V_inf into (u,v,w), then

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Aerodynamic Derivatives wrt to u,v,w

This is normal flight dynamics process. Assuming that you would decompose V_inf into (u,v,w), then

Jan 28

Cindy Chen, Rob McDonald10

Jan 28

spikes at wingtips in panel method solution

Start by deleting a bunch of the sections -- your center body is way over determined. Your chord

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spikes at wingtips in panel method solution

Start by deleting a bunch of the sections -- your center body is way over determined. Your chord

Jan 28

Syed Mujahid, … Rob McDonald6

Jan 27

How to make a fuselage surface smooth

I would attempt to model this fuselage with four cross sections. One at the nose, one at the tail,

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How to make a fuselage surface smooth

I would attempt to model this fuselage with four cross sections. One at the nose, one at the tail,

Jan 27

Cindy Chen, Rob McDonald3

Jan 27

Analyzing a blended wing-body with both VLM and panel method

The screenshot I showed was just for illustrative purposes. Attached is the actual geometry I want to

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Analyzing a blended wing-body with both VLM and panel method

The screenshot I showed was just for illustrative purposes. Attached is the actual geometry I want to

Jan 27

Mano, … Rob McDonald5

Jan 27

Design of toroidal propeller

The center of that is a body of revolution, the blades are not. If you want to model the hub with a

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Design of toroidal propeller

The center of that is a body of revolution, the blades are not. If you want to model the hub with a

Jan 27

T T, Rob McDonald4

Jan 27

The Aerodynamic calculation results displayed in VSPAERO results manager revealed discontinuity of graph curve: lift coefficients Cl vs. wing span coordinate Y in vicinity of transition zone between flaps/ailerons and wing.

The air density is used as specified, but your units made it of magnitude 1e-9 -- which does not

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The Aerodynamic calculation results displayed in VSPAERO results manager revealed discontinuity of graph curve: lift coefficients Cl vs. wing span coordinate Y in vicinity of transition zone between flaps/ailerons and wing.

The air density is used as specified, but your units made it of magnitude 1e-9 -- which does not

Jan 27

José Alfredo Rosas, … Rob McDonald12

Jan 27

Difference between XSECSURF and XSEC?

You should start a new thread rather than posting on a 5 year old one. The XSec Parms are available

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Difference between XSECSURF and XSEC?

You should start a new thread rather than posting on a 5 year old one. The XSec Parms are available

Jan 27

Jan 24

Not properly formulated questions on OpenVSP discussion group - please remove my 2 threads

Good morning, i sent Not properly formulated threads on OpenVSP discussion group - there were not

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Not properly formulated questions on OpenVSP discussion group - please remove my 2 threads

Good morning, i sent Not properly formulated threads on OpenVSP discussion group - there were not

Jan 24

Jan 24

he Aerodynamic calculation results displayed in VSPAERO results manager revealed discontinuity of graph curve: lift coefficients Cl vs. wing span coordinate Y in vicinity of transition zone between flaps/ailerons and wing.

Good morning everyone, i am especially interested in applying of aircraft wing's pressure

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he Aerodynamic calculation results displayed in VSPAERO results manager revealed discontinuity of graph curve: lift coefficients Cl vs. wing span coordinate Y in vicinity of transition zone between flaps/ailerons and wing.

Good morning everyone, i am especially interested in applying of aircraft wing's pressure

Jan 24

Jan 24

There is an option or setting in the VSPAERO to find Angle of Attack of the wing for corresponding equilibrium between estimated Total Lift Force Lz of analyzed wing with Weight Force of the wing?

There is an option or setting in the VSPAERO to find Angle of Attack of the wing for corresponding

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There is an option or setting in the VSPAERO to find Angle of Attack of the wing for corresponding equilibrium between estimated Total Lift Force Lz of analyzed wing with Weight Force of the wing?

There is an option or setting in the VSPAERO to find Angle of Attack of the wing for corresponding

Jan 24

Jan 24

Discontinuity of graph curve: lift coefficients Cl vs. wing span coordinate Y in vicinity of transition zone between flaps/ailerons and wing

I am especially interested in applying of aircraft wing's pressure distribution estimated in

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Discontinuity of graph curve: lift coefficients Cl vs. wing span coordinate Y in vicinity of transition zone between flaps/ailerons and wing

I am especially interested in applying of aircraft wing's pressure distribution estimated in

Jan 24

Mike Novikov, … Steven Zhu10

Jan 23

Adjoint Optimization

Steven, thank you for your answer. I use OpenVSP 3.46. I am starting VSPAero via cmd with vspaero_opt

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Adjoint Optimization

Steven, thank you for your answer. I use OpenVSP 3.46. I am starting VSPAero via cmd with vspaero_opt

Jan 23

Luís Filipe De Almeida E Silva, Rob McDonald3

Jan 22

Coefficients do not change in *.lod file when ref. area is changed

Thanks, Rob. I made a test using a simple rectangular wing and what you said seems to be correct.

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Coefficients do not change in *.lod file when ref. area is changed

Thanks, Rob. I made a test using a simple rectangular wing and what you said seems to be correct.

Jan 22

Jan 22

OpenVSP 3.47.0 Released

The gap since the last release (3.5mo) is a bit longer than usual (1-2mo). While some of that gap is

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OpenVSP 3.47.0 Released

The gap since the last release (3.5mo) is a bit longer than usual (1-2mo). While some of that gap is

Jan 22

Mike Novikov, … Rob McDonald5

Jan 13

High Cp value around trailing edge

Thank you, Rob. Noted! понедельник, 12 января 2026 г. в 21:55:26 UTC+4, Rob McDonald: Those high

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High Cp value around trailing edge

Thank you, Rob. Noted! понедельник, 12 января 2026 г. в 21:55:26 UTC+4, Rob McDonald: Those high

Jan 13

Miguel Aguirre, Rob McDonald2

Jan 12

VSP AERO - ERROR IN STEADY MODE

There is no way for the user to change the size of the perturbations. The perturbations were reduced

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VSP AERO - ERROR IN STEADY MODE

There is no way for the user to change the size of the perturbations. The perturbations were reduced

Jan 12

Violet Philip, Rob McDonald2

Jan 7

Did the CG end up where you would expect it to be? During the early phases of design (or when a model

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Did the CG end up where you would expect it to be? During the early phases of design (or when a model

Jan 7

Gabriel Kern, Rob McDonald4

Jan 7

Crash Using FEA Structures

No workaround known yet. Unfortunately, I'm having difficulty recreating this problem on my Mac,

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Crash Using FEA Structures

No workaround known yet. Unfortunately, I'm having difficulty recreating this problem on my Mac,

Jan 7

Lorenzo Naddei, … Rob McDonald6

Jan 6

CAN'T DEFLECT A SURFACE

Brandon, You are supposed to be able to assign surfaces to multiple groups -- it is a bug that you

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CAN'T DEFLECT A SURFACE

Brandon, You are supposed to be able to assign surfaces to multiple groups -- it is a bug that you

Jan 6

elephantwalker smith, … Rob McDonald11

Jan 5

The camber parameterization works with: NACA 4-Digit NACA 6-Series NACA 4-Digit Modified NACA 5-Digit

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The camber parameterization works with: NACA 4-Digit NACA 6-Series NACA 4-Digit Modified NACA 5-Digit

Jan 5

Tim Cuatt, Rob McDonald4

12/29/25

Bitmasking in VSPScript?

OK, thanks for the clarification. I guess AngelScript doesn't automatically interpret ints as

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Bitmasking in VSPScript?

OK, thanks for the clarification. I guess AngelScript doesn't automatically interpret ints as

12/29/25

danie...@gmail.com, Rob McDonald2

12/23/25

Difficulty getting prop model to work

You can't do propeller analysis with the 'Shown' Set. You must put the Prop into another

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Difficulty getting prop model to work

You can't do propeller analysis with the 'Shown' Set. You must put the Prop into another

12/23/25

12/18/25

VSP Python API RemoveControlSurfaceGroup

Hi everyone, I'm looking for a function to remove a ControlSurface group that I create by using

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VSP Python API RemoveControlSurfaceGroup

Hi everyone, I'm looking for a function to remove a ControlSurface group that I create by using

12/18/25

Matin Nafari, … Tad Chichester3

12/17/25

Loads of Individual Surfaces

Please do Rob. I have developed a suite of python apps for FAR 23 loads that depend on the pre-v3.45

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Loads of Individual Surfaces

Please do Rob. I have developed a suite of python apps for FAR 23 loads that depend on the pre-v3.45

12/17/25

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