XV-15 Rotor Blade Analysis using the Blade Element Disk Method

XV-15 Rotor Blade Analysis using the Blade Element Disk Method#

Highlights#

In this case study we are going to show you how to:

  • Simulate an XV-15 tiltrotor airplane in both hovering helicopter mode and forward flight airplane mode using the steady BET Disk solver in Flow360

  • Convert dimensional input quantities to nondimensional quantities in the Flow360 configuration json file

  • Convert nondimensional quantities in the output to dimensional quantities

Introduction#

The development of the XV-15 tiltrotor was launched by the NASA Ames Research Center in collaboration with Bell Helicopters in the late 1960s and early 1970s. It has become the foundation of many VTOL aircrafts today. Unlike typical helicopter rotors, tiltrotor blades demand a compromised design to operate efficiently in both helicopter and propeller modes. Hence, the blades of the XV-15 tiltrotor have high twist, high solidity and small rotor radius. In this case study, we will apply our Blade Element Theory (BET) Model based solver in Flow360 to evaluate the performance of the XV-15 rotor in both helicopter hovering mode and airplane mode.

../../_images/XV-15_N703NA_USCG.jpg

Fig. 140 The Bell Textron XV-15 Tiltrotor aircraft prepares to land (source: United States Coast Guard)#

The definition of the cross sections of the rotor blade is shown in Table 23. The main geometric characteristics of the XV-15 rotor blades are listed in Table 24.

Table 23 Cross sections of XV-15 rotor blade#

r/R

Airfoil

0.09

NACA 64-935

0.17

NACA 64-528

0.51

NACA 64-118

0.80

NACA 64-(1.5)12

1.00

NACA 64-208
Table 24 Geometric characteristics of XV-15 rotor#

Parameter

Value

Number of blades

3

Rotor radius

150 inches

Reference blade chord

14 inches

Aspect ratio

10.71

Rotor solidity

0.089

Linear twist angle

-40.25 degree

The radial chord and twist distribution is shown in Fig. 141.

../../_images/xv15_twist_chord_definition.png

Fig. 141 XV-15 rotor blade’s twist and chord radial distribution#

More information about the geometry and a high-fidelity detached eddy simulation done using Flow360 can be found at

Feilin Jia, John Moore and Qiqi Wang, 2022, Assessment of Detached Eddy Simulation and Sliding Mesh Interface in Predicting Tiltrotor Performance in Helicopter and Airplane Modes

In this case study, the steady Navier-Stokes solver coupled with the Blade Element Theory Disk method is used to simulate the XV-15 rotor blades under two flight conditions: helicopter hovering mode and airplane mode. In order run cases in a few minutes, compared to the high fidelity unsteady simulations with full rotor geometry in the above paper, the mesh for this BET Disk example is much coarser. The mesh used in the current case study contains only 592K nodes. An overview of a slice of the mesh is shown below

mesh1 mesh2

mesh3 mesh4

Overview of volume mesh used in BET Disk simulations of XV-15 rotor, successively zooming in from top left->top right->bottom left->bottom right.

The freestream quantities are shown below. These quantities are needed to set up the nondimensional variables in the flow360 case configuration and translate the nondimensional output variables into dimensional values. More information on nondimensionalization in Flow360 can be found at Nondimensional Inputs and Nondimensional Outputs. In the above mesh, the grid unit \(L_{gridUnit}=1\,\text{inch}=0.0254\,\text{meter}\). In this case study, the freestream conditions are set to standard sea level values as shown in Table 25

Table 25 Sea-level air properties#

air property

sea level - \(288\,\text{Kelvin}\)

density, \(\rho_{\infty}\)

\(1.225\, kg/m^3\)

speed of sound, \(C_{\infty}\)

\(340.3\,m/s\)

Caution

In some simulations, the freestream is not set to be at standard sea level on purpose. For example, in the “case 1a” from 3rd AIAA CFD High Lift Prediction Workshop, the viscosity of the freestream is adjusted to analyze the full-scale geometry at wind tunnel conditions, so please set the freestream properties based on your requirements.

Helicopter Hovering Mode#

In helicopter hovering mode, the freestream velocity is zero. Five blade collective angles are considered in the current study: \(0^o, 3^o, 5^o, 10^o, 13^o\) at \(r/R=0.75\), corresponding to low, medium and high disk loadings. The flow conditions are:

  • Tip Mach Number, defined as \(U_\text{tip}/C_{\infty}\), is 0.69, so \(U_\text{tip}=0.69C_\infty\).

  • Reynolds Number (based on reference chord (14 inch) and blade tip speed) = \(4.95\times 10^6\).

  • Reference Temperature = 288.15 K.

Here are some points to set up the case configuration file:

  1. freestream->Mach is set to 0, because freestream velocity is zero.

  2. freestream->MachRef has to be a non-zero number because the above “Mach” is 0. Theoretically, this value could be arbitrary, but we set it equal to the tip Mach number (0.69) for convenience.

  3. Either freestream->Reynolds or freestream->muRef should be given to set a proper freestream viscosity. Both options are explained below:

    • Option 1: set freestream->Reynolds. The freestream->Reynolds is based on grid unit as the reference length, thus it is mesh dependent. It’s definition is \(\rho_\infty U_\text{ref} L_\text{gridUnit}/{\mu_\infty}\). In the case description, we know the Reynolds number based on tip speed and reference chord is \(4.95\times 10^6\), so we must convert the value from the reference chord used to the \(L_{gridUnit}\) in the mesh.

    (2)#\[\frac{\rho_\infty U_\text{tip} \text{chord}_\text{ref}}{\mu_\infty} = \frac{\rho_\infty \left(0.69 C_\infty\right) \text{chord}_\text{ref}}{\mu_\infty} = 4.95\times 10^6\]

thus the freestream->Reynolds is calculated by:

(3)#\[\begin{split}\text{freestream->Reynolds}&=\frac{\rho_\infty U_\text{ref} L_\text{gridUnit}}{\mu_\infty} = \frac{\rho_\infty\cdot \text{MachRef} \cdot C_\infty L_\text{gridUnit}}{\mu_\infty} \\ &=\frac{\rho_\infty \left(0.69 C_\infty\right) \text{chord}_\text{ref}}{\mu_\infty}\times\frac{\text{MachRef}}{0.69}\times\frac{L_\text{gridUnit}}{\text{chord}_\text{ref}} \\ &= 4.95\times 10^6 \times \frac{0.69}{0.69}\times \frac{1\, \text{inch}}{14\, \text{inch}} = 3.3536\times10^5\end{split}\]

The freestream->Reynolds is \(3.3536\times10^5\)

  • Option 2: set freestream->muRef. The “muRef” here is a nondimensional quantity, it is mesh dependent because it depends on \(L_{gridUnit}\). Its definition is

(4)#\[\text{freestream->muRef} = \frac{\mu_\infty}{\rho_\infty C_\infty L_\text{gridUnit}}\]

If you already know the Reynolds number then you could use the following equation to get the freestream->muRef:

(5)#\[\begin{split}\text{freestream->muRef} &= \frac{\rho_\infty U_\text{tip}\text{Chord}_\text{ref}/Re}{\rho_\infty C_\infty L_\text{gridUnit}} =\frac{\rho_\infty \left(0.69 C_\infty\right) \text{14 inch}}{\rho_\infty C_\infty \text{1 inch} \cdot 4.95\times10^6} \\ &=\frac{0.69\cdot \text{14 inch}}{\text{1 inch} \cdot 4.95\times 10^6} = 1.95152\times10^{-6}\end{split}\]

Therefore, the freestream->muRef is \(1.95152\times10^{-6}\)

  1. BETDisks->omega is the nondimensional angular speed of the rotor blades. Its definition is

    (6)#\[\text{BETDisks->omega} = \Omega\cdot\frac{L_\text{gridUnit}}{C_\infty}\]

Because we know \(\Omega=\frac{U_\text{tip}}{\text{Radius}}\),

(7)#\[\begin{split}\text{BETDisks->omega} &= \frac{U_\text{tip}}{\text{Radius}}\cdot\frac{L_\text{gridUnit}}{C_\infty} = \frac{0.69C_\infty\cdot \text{1 inch}}{\text{150 inch} \cdot C_\infty}\\ &= 0.69/150 = 0.0046\end{split}\]

Therefore, BETDisks->omega is 0.0046

After setting up the case configuration file, the case is ready to submit. The 592K-node mesh file, and its corresponding mesh and case configuration files can be downloaded via the following links:

Note

The only difference between the configuration files of the above 5 cases is the BETDisks/twists distribution.

For detailed instructions on how to upload a mesh, run a case and download the results, please refer to the Quick Start section of this documentation - these details will not be covered in this case study.

Some tips on setting the input quantities related to BET can be found in the BETDisks section of the knowledge base. Please note that there is no hub in the high fidelity detached eddy simulation of the XV-15 rotor blades in our paper mentioned above, so to match the model used in the high fidelity simulations, the chord length in \(r<0.09R\) should be set to 0 in the BET simulation configuration files. I.e. the chord length is set to 0 right before the first cross section (\(r=0.09R\)). This setting leads to a radial distribution similar to “chords_distribution_1” shown in BETDisks.

The forces and moments related to the BET Disk are saved in the “bet_forces_v2.csv” file. A detailed description can be found at BET Loading Output. Here we will convert those non-dimensional values into dimensional values:

  1. thrust and torque.

Because the axial direction of the rotor is in the Z axis, the thrust is saved as “Disk0_Force_z” and the torque is saved as “Disk0_Moment_z” in the .csv file. The dimensional thrust and torque can be calculated by Eq.(60) and Eq.(61):

(8)#\[\begin{split}\text{Thrust} &= \text{Disk0_Force_z}\cdot \rho_\infty C^2_\infty L^2_\text{gridUnit} \\ &= \text{Disk0_Force_z}\cdot 1.225 kg/m^3 \times 340.3^2 m^2/s^2 \times 0.0254^2 m^2 \\ &= \text{Disk0_Force_z}\cdot 91.5224 N\end{split}\]
(9)#\[\begin{split}\text{Torque} &= \text{Disk0_Moment_z}\cdot \rho_\infty C^2_\infty L^3_\text{gridUnit} \\ &= \text{Disk0_Moment_z}\cdot 1.225 kg/m^3 \times 340.3^2 m^2/s^2 \times 0.0254^3 m^3 \\ &= \text{Disk0_Moment_z}\cdot 2.324669 N\cdot m\end{split}\]

The convergence history of the dimensional thrust and torque using steady BET Disk solver is shown in following figures:

hover_history_thrust hover_history_torque

Loading convergence of BET Disk simulation in hovering helicopter mode at various pitch angles.

  1. sectional thrust and torque.

In the “bet_forces_v2.csv” file, the sectional thrust coefficients are provided. The process to convert the nondimensional Ct into its physical dimension, i.e. sectional thrust per unit span in SI is very similar to the one shown above. We need the dimensional quantities mentioned in Eq.(62) and Eq.(63) to compute the dimensional sectional thrust:

  • Radius of the rotor disk \(R = 150\times L_{gridUnit} = 3.81\,\text{meter}\)

  • rotating angular speed \(\Omega = V_{tip}/R = Mach_{tip}*C_{\infty}/R = 61.6237\, \text{rad/second}\)

  • reference chord \(\text{chord}_{\text ref}=14\times L_{gridUnit} = 0.3556\, \text{meter}\)

If we assume that we want to calculate the sectional thrust and torque at the first disk’s first blade’s second radial location, i.e. Disk0_Blade0_R1:

(10)#\[ \begin{align}\begin{aligned}&C_t = \text{Disk0_Blade0_R1_ThrustCoeff}\\&C_q = \text{Disk0_Blade0_R1_TorqueCoeff}\\&r = \text{Disk0_Blade0_R1_Radius}*L_\text{gridUnit}\\&\text{Thrust per unit blade span}_\text{Disk0_Blade_R1} = C_t\times\frac{1}{2}\rho_\infty\times\Omega^2 r^2 \text{chord}_\text{ref}\times R/r\\&\text{Torque per unit blade span}_\text{Disk0_Blade_R1} = C_q\times\frac{1}{2}\rho_\infty\times\Omega^2 r^2 \text{chrod}_\text{ref} R\times R/r\end{aligned}\end{align} \]

As a comparison example between the high fidelity full-rotor unsteady simulation and the BET Disk steady simulation, the physical sectional thrust on a blade per unit span, for the \(\theta_{75}=10^o\) case, is shown below

hover_sectionalThrust hover_history_thrust_compare

Sectional thrust distribution and history of total thrust in hovering mode, \(\theta_{75}=10^o\).

The biggest differences between these high fidelity simulations and these BET Disk simulations are near the tip regions where blade-vortex interactions are strong. The flow around the tip can be highly three dimensional, making a BET Disk approximation locally inaccurate. This effect is proportional to the blade disk loading, thus it is larger at hovering or near-hovering conditions when the thrust is higher then in forward flight. Even then, the total thrust of the three blades in hover, compared to the Flow360 high fidelity unsteady simulation, is ~8% different. This level of accuracy makes the BET Disk a useful tool in the preliminary design stages.

To provide another overview of the BET disk accuracy; If we look at the propeller efficiency in hovering mode, the thrust coefficient, the torque coefficient and the figure of merit defined in Eq.(11) and compare them with several experimental data and numerical prediction of high-fidelity DES simulations, we get the graphs below:

(11)#\[ \begin{align}\begin{aligned}C_T &= \frac{\text{Thrust}}{\rho_\infty \left(\Omega R\right)^2A}\\C_Q &= \frac{\text{Torque}}{\rho_\infty \left(\Omega R\right)^2AR}\\\text{Figure of Merit} &= \frac{C_T^{3/2}}{\sqrt{2}C_Q}\end{aligned}\end{align} \]

where \(R\) is rotor disk radius and \(A\) is rotor disk area, i.e. \(\pi R^2\)

hover_CT_CQ hover_CT_FOM

Comparison on thrust and torque coefficient and figure of merit in hovering mode at various pitch angles.

Airplane Mode#

In airplane mode, four blade collective angles are considered: \(26^o, 27^o, 28^o, 28.8^o\) at \(r/R=0.75\). The flow conditions are:

  • Tip Mach Number = 0.54.

  • Reynolds Number (based on reference chord and tip speed, with no account for the inflow velocity) = \(4.5\times 10^6\).

  • Reference chord = 14 inch.

  • Reference Temperature= 288.15 K.

  • Advance ratio (defined as inflow speed over tip speed) = 0.337

The mesh file and mesh configuration file are the same as the files used in the helicopter hovering example above. The case configuration files, however, are different:

The convergence history of the thrust coefficients and torque coefficients using the steady BET Disk solver are shown below

airplane_T_history airplane_Q_history

Convergence history of thrust coefficient and torque coefficient in airplane mode at various pitch angles.

As an example, similarly to the helicopter hovering case shown above, the physical sectional thrust for the \(\theta_{75}=26^o\) case is shown below. We have comparisons to the high fidelity DES simulation both on a blade per unit span basis and for the total force.

Note

Please note the non-zero origin of the Y axis on the right plot of total force.

airplane_sectionalThrust airplane_thrust_history

Sectional thrust distribution and thrust history in airplane mode at \(\theta_{75}=26^o\).

To provide an overview of power efficiency in airplane mode at various pitching angles, the figure below shows the comparison of the thrust coefficient, torque coefficient and propeller propulsive efficiency, defined in Eq.(12), between the BET Disk and high fidelity simulations.

(12)#\[\eta = \frac{C_T \cdot V_\infty}{C_Q \cdot V_\text{tip}}\]

airplane_CTCQ airplane_CTeta

Comparison of thrust coefficient, torque coefficient and propulsive efficiency in airplane mode at various pitch angles.