Engineering Trying to design Wind Turbine Blades

AI Thread Summary
To design wind turbine blades using Blade Element Momentum Theory (BEMT), it is essential to assume a chord distribution to calculate the Reynolds number, which is necessary for determining lift and drag coefficients. The design process involves iterative adjustments to the chord distribution based on the results obtained. Initial values for axial and angular induction factors are typically set to zero, and the calculations proceed from there. The user shared specific data and results from their calculations, including airfoil types, lift and drag coefficients, and various aerodynamic factors. The discussion emphasizes the importance of iteration in achieving a feasible blade design.
jonagad
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Homework Statement
Blade Element Momentum
Relevant Equations
Reynolds numer:
Re=((V)*(ρ)*(c))/μ
Where:
V:wind velocity
ρ: density
c: chord
μ: Dynamic viscosity
Hello, I'm trying to follow the instructions from the book "Aerodynamics of Wind Turbines"-Martin O.L. Hansen, to design a blade, the method it's the BEM accounting for the tip loss (Prandtl) and Glauert corrections, but I can't get it right, for the Cl (lift coefficient) and Cd (drag coefficient) I need the Reynolds number, but in order to calculate de Re, I need the chord, how can I give a value to the chord?
 
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You need to assume a chord distribution. See what comes out and if not feasible / desirable, choose another chord distribution. That's the design iteration loop.
 
Ps: it is usually referred to as BEMT (Blade Element Momentum Theory), not to be confused with BEM (Boundary Element Method)
 
Arjan82 said:
You need to assume a chord distribution. See what comes out and if not feasible / desirable, choose another chord distribution. That's the design iteration loop.
Ohh, I see, that´s exactly what I was doubting, thank you for responding, i will do that.

This is what I have, if you want to check it out:
Data:
a: Axial Induction factor
a´: Angular induction factor
Both a and a´ usually are =0 initially.
Then it´s an iterative process
U_1=5.17m/s
Ω=25rpm2.61799388rad/s
R=1.25m
B=3
a_c=0.2
Results:
AirfoilS823S823S823S822S822S822S822S822
No12345678
Section0.20.30.40.50.60.70.80.9
a=0.1999990.1999990.1999990.1999990.1999990.1999990.1999990.199999
a´=00000000
r=0.250.3750.50.6250.750.87511.125
λ_r=0.126595450.189893170.25319090.316488620.379786350.443084070.506381790.56967952
tanφ=6.319350414.212900273.15967522.527740162.106450141.805528691.57983761.40430009
φ=1.413853591.337743211.264282191.194079911.12756641.06499871.006481690.95199662
f=6.07465913.597248682.359996671.613115581.106964680.734871670.443810430.2046056
F=0.99853550.982555070.939800340.872288560.785524250.681587490.556552640.39350817
α(°)=8.98.98.99.39.39.39.39.3
α(rad)=0.15533430.15533430.15533430.162315620.162315620.162315620.162315620.16231562
θ_p=1.258519291.182408911.108947891.031764290.965250780.902683080.844166070.789681
C_l1.21.21.211111
C_d0.0180.0180.0180.010.010.010.010.01
C_n0.205337880.294652390.379245540.377167910.437893230.493253230.54328640.5882036
C_t1.182438311.16340191.138638140.926198880.89908260.869943250.839606990.80877471
supposed chord=0.30.30.30.30.30.30.30.3
σ=0.57295780.381971860.28647890.229183120.190985930.163702230.143239450.12732395
K=33.120011333.057554331.450295334.902325430.660727525.83824520.4240713.9456387
a (if≤a_c)=0.031133240.03119390.03284040.02949650.033714610.040260490.051482520.07724609
a (if>a_c)=-0.014839980.028547770.029921870.027118490.030646570.035968280.044683980.06296168
a´=-11.12852991.012833760.431917720.216319250.1642240.140566920.13577140.16071096
dF_N=0.58509770.432562060.577875660.608327260.741833540.879084531.013705671.11762702
dQ=3.369285471.707922751.735000681.493849351.5231331.550428071.566603481.53672719
dr=0.250.1250.1250.1250.1250.1250.1250.125
U_rel=5.071369575.147896745.244662675.395874925.530058395.672061745.803662125.85659519
dF_T=4.492380631.518153551.156667120.796719650.6769480.590639260.522201160.45532658
dF_L=1.139775480.587216770.609500290.537627280.564698950.59407250.621959050.6333561
dF_D=0.017096630.008808250.00914250.005376270.005646990.005940720.006219590.00633356
 
Of course, thank you
Arjan82 said:
Ps: it is usually referred to as BEMT (Blade Element Momentum Theory), not to be confused with BEM (Boundary Element Method)
 
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