NACA 0012 Airfoil CFD simulation in Fluent and validation with experimental data

[@pradiparyal2857]

Take a bow sir. Such a brilliant tutorial.

[@lnr6110]

Can you please make a video on Analysis of aerofoil (NACA0012) with gurney flap in CFD

[@gautam8993]

how to split the domain into two parts (one for laminar and one for turbulent) according to the tranisition point on upper surface and lower surface of an airfoil? i want to force the laminar domain into laminar zone in fluent cell zone conditions.

[@saifahmed4704]

If instead of an airfoil, we want to run the simulation for a 2D cylinder, will there be any significant changes regarding the blocking parameters?

[@CFD_Mechanic]

Almost similar For further knowledge on ICEMCFD you can refer to www.udemy.com/ansys-icemcfd-hexa-become-guru-in-hexa-mesh-generation/?couponCode=NINENINENINE

[@ras22king]

Thanks for the great video. My only question that the case were done for 3000000 Reynold number while the experimental were done for 6000000

[@CFD_Mechanic]

It is done for 3 million and experimental data is also for 3 million

[@ras22king]

@@CFD_Mechanic from wing section theory book. If not may you tell the reference

[@CFD_Mechanic]

@@ras22king yes same reference

[@ras22king]

One last question, how to set mach and number together. I tried but the using the velocity from mach number and changing viscouty and density for constant Reynold numb but still the results are really far from the experiment

[@alibnalabd9859]

Hi, Can I get the experimental values ​​as a pdf?

[@akarshshetty9262]

To validate analysis against experimental data, is the starting point choosing a specific value of Reynolds Number? What is the idea behind choosing a particular Reynolds Number

[@CFD_Mechanic]

This is most commonly used value of Reynolds number in open literature.

[@beautifulplaces4900]

please upload video with airfoil having some angle of attack.There are a lot of videos with zero angle of attack!

[@TheShashi02]

sir please make a video for" drag reduction on airfoil with vortex generator"

[@jonasschmelz3611]

nice tutorial, but have you recognized that the shape of the cut section in the control volume is not exact like the profile? it has some edges. is this only presentation error or is the boolean operation not accurate?

[@CFD_Mechanic]

It is limitation of visualization on screen

[@SanthoshKumar-bm9kh]

why do you have the pressure forces in the negative value ?

[@arismerdis1381]

Hi, Thank you so much for this really helpful tutorial. I have a problem with results, I completely followed your tutorial with the same mesh, but I don't know why my results are really bad, Cd is around 2 while it should be 0.005, could you please help me?

[@CFD_Mechanic]

check your reference conditions.

[@upskiekobunski]

really? the ICEM model tutorial was very very very fast..

[@farcfd4394]

it was a simple :D

[@renelomasrodriguez7254]

thank you so much... continue please making this kinds of videos. are greats

[@aidealczar6075]

Hello Sir, Why did you chose the specification method to KL, Intensity, and Length Scale at 31:03? Also the value for backflow turbulent length scale is by default 1 but in the video it is 0.3

[@CFD_Mechanic]

0.3 * chord lenght = 0.3

[@aidealczar6075]

@@CFD_Mechanic thank you and just one more thing, how many iterations that you had to do for k kl omega with 2nd upwind? I had to do over 10k of iterations. Is this normal?

[@CFD_Mechanic]

@@aidealczar6075 yes normal.

[@aidealczar6075]

@@CFD_Mechanic Thank you Sir, since we only need to capture the boundary layer aswell as the wake region, do you think a hybrid mesh (something like yours covering near the airfoil and wake region+ triangles on the outside) will reduce computation time while maintaining accuracy?

[@KarthiKeyan-pd1xb]

Is meshing method different for transition solvers ? what are the parameters should consider for Low Re transition solvers ?

[@CFD_Mechanic]

all things are same. but the region of transition is meshed carefully . connect with on Facebook facebook.com/farcfd

[@ing.anthony7097]

Hello plz I have a presentation to make on Wednesday about airfoils (wind turbines)... the only thing I don’t know is how to determine the rotating speed or the rpm of the rotor if I know the wind velocity is 8m/s... how does it affect a certain airfoil? If for instance I have a NACA 4418... a wind speed of 8m/s will result in how much RPM ? Plz this is urgent

[@CFD_Mechanic]

You have to make elementary study. Please go to chapter no. 10 Wind Turbines in Fluid Mechanics and Thermodynamics of Turbomachinery Sixth or 7th edition by Dixon.

[@pradipchaughule3464]

Warning: Mesh has uncovered edges. ANSYS Flunet needs a complete boundary or it will give a variety of errrors and not read in the mesh! why this came?

[@jimjosephkurian5492]

Hello sir. Could u state the process down to obtain SPL vs frequency, SPL vs locations and Frequency vs location???. This is in relation to steps followed by you in video for k-kl omega model. Thanks

[@CFD_Mechanic]

complete process is described in tutorial on unsteady flow over 2d cylinder

[@raulfelipecorralesflores3439]

Hello Advanced Engineering Solutions, I'm already on tour courses (udemy) actually I bought both Levels. I've a question about The last solution that you showed. Which turbulence Model did you use? (the name is Six equation Model). I need to get this results for my Thesis (Cd around 0,006).

[@CFD_Mechanic]

It was transition SST model with Y plus less than 1

[@avs341]

thank you so much sir it was very informative

[@150486sarah]

can you show how to create a surface for open airfoil

[@CFD_Mechanic]

Sarah a'fifah it is shown in this tutorial...

[@safirhaddad5402]

Thank you, you really help me dude 😁

[@aajad2398]

Safir Haddad do u know how to close the airfoil

[@ahadjizin]

great work thank you very much

[@CFD_Mechanic]

thankyou

[@akkingkong1]

sir, can u plz tell how to create farfield( ff) u directly applied it in fluent ->boundary condition->ff. how to make it because mine only 1)surface_body 2)int_aerofoil(it contains the mesh)

[@CFD_Mechanic]

check at 10.18

[@yashmurthy1019]

For calculating y+ value how is boundary layer length taken as chord length?

[@CFD_Mechanic]

it is not taken as chord length, rather based on chord we calculate Reynolds number and use formula to find out the boundary layer thickness.

[@CFD_Mechanic]

It is not.

[@joellesalamoun8768]

does the mesh apply on unsymmetrical airfoils as well?

[@CFD_Mechanic]

yes

[@ravikumarlanka9193]

Hi can you please re do this video if possible from ICM section on words it is bit confusing please?

[@CFD_Mechanic]

i will try. Although we have made new tutorial with better physics understanding and including detailed discussion on geometry creation of airfoil and ICEM CFD hexa part. We are going to make them online very soon

[@aajad2398]

How to close the airfoils

[@praveenkumarp2182]

i want find out cl & cd for 3d wing. my flow is x direction.can i use x direction projected area for reference value.

[@CFD_Mechanic]

use area = chord length * wing span

[@privateprofile3517]

what changes to make if the foil is near the free surface of an air water interaction and the foil in in water phase.

[@CFD_Mechanic]

i cannot exactly say anything at this moment. Whatever changes it requires, that should not radically change the meshing strategy in ICEM CFD.

[@privateprofile3517]

Advanced Engineering Solutions I meant about the BC In fluent and generally the change in the physics behind it.

[@atifmohamed2379]

can i have the experimental data file please ?

[@rahulprajapati8921]

what kind of mesh we have to generate, if our airfoil have blunt egde??

[@CFD_Mechanic]

C type or full O type

[@shivamhankare8886]

Can you upload for airfoil in ground effects for a rectangular domain ?

[@CFD_Mechanic]

Hi. Do you have geometry and boundary conditions for such case?

[@MrSarfaraznawazshaha]

when i import the mesh only the inlet velocity boundary condition is not coming

[@CFD_Mechanic]

***** did you define the part for it? may be you need to recompute/regenerate the mesh...

[@MrSarfaraznawazshaha]

turbo engineer yes i have defined the part. still having the same problem

[@avs341]

+sarfaraz nawaz Shaha bro i had the same problem . it can be resolved by blocking properly ( i mean block each edge separately).

[@eriksugianto7629]

I have a problem when I uploaded the .txt file appears Error reading coordinates files, I have tried some trial error, but the results are same. please advise, thank you

[@nathanoliveira7889]

try to exchange commas and points

[@ovalwingnut]

Ah..... What did he say?

[@KarthiKeyan-pd1xb]

can we carried out for all airfoils

[@CFD_Mechanic]

yes

[@ayushsharma1103]

Great tutorial, but your ICEM part was too fast to understand. 5/10

[@hassan_k_qissay]

It was never meant for you to understand

[@metaloper]

You are in a rush?

[@CFD_Mechanic]

Really. If you need very detailed step by step guidance please have a look at this www.udemy.com/mastering-ansys-cfd/?couponCode=CFDJUNE

[@metaloper]

I just find funny that almost every cfd tutorial seems like a F1 race. Thanks for the link.

[@simplyball4260]

LIKE

[@perecollfdz]

Like si vens de la UPC per fer el treball de Aerodinamica...

[@derbazkhalil5290]

DEAR I HAVE REYNOLDS NO ONLY FOR RESEARCH PAPER ( SANDIA80-2114 ) FOR NACA 0012 SO HOW CAN PUT THE BOUNDARY CONDITION IN FLUENT ANSYS THAT NEEDS VELOCITY DATA ? CAN ANY BODY HELP ME

[@CFD_Mechanic]

It is simple. Find out value of velocity from Reynolds number.

[@downtester]

Can u send to me excel files? THX

[@niklove009]

This is the error i am getting can someone tell me what i am doing wrong? Cell is missing face: Cell 16815, zone 11, at location ( 2.44157e+01, -1.35240e+01). Clearing partially read grid. Error: Build Grid: Aborted due to critical error. Error: Build Grid: Aborted due to critical error. Error Object: #f

[@CFD_Mechanic]

+nikhit gupta Mesh error. Need to check it in ICEM for missing edges/faces etc. More likely a issue of association.

[@niklove009]

thank you

[@brandon_xavier_cf8388]

Hello I did the analytical of a NACA 4415 in drag fluid and lifting the results these Cl = 7.2870e-04 and Cd = 1.7649e-05 The experimental results are Cl = 0.787785 Cd = 0.01218 I would like to know how to interpret these fluid values and whether they are correct or approximate with the experiments