% =========================================================================
% MIT OpenProp_v2.4.6
% Last modified: *
% =========================================================================
%
% MIT = Massachusetts Institute of Technology (Cambridge, MA, USA)
% OpenProp = Open-source Propeller Design and Analysis Program
%
%
%
% =================== INFORMATION TAKEN FROM OpenProp_v1 ==================
%
% ------------------- Copyright 2007 Brenden Epps et al -------------------
% This program is free software. You can redistribute it and/or modify it
% under the terms of the GNU General Public License version 2, as published
% by the Free Software Foundation. This program is distributed in the hope
% that it will be useful, but WITHOUT ANY WARRANTY; without even the
% implied warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.
% See the GNU General Public License for more details.
%
% ------------------------------- References ------------------------------
% 1) J.S. Carlton, "Marine Propellers & Propulsion", chapter 3, 1994.
% 2) W. Coney, "A Method for the Design of a Class of Optimum Marine
% Propulsors", Ph.D. thesis, MIT, 1989.
% 3) J. Kerwin, "Hydrofoils and Propellers", MIT Course 2.23 notes, 2007.
% 4) J.W. Wrench, "The Calculation of Propeller Induction Factors", David
% Taylor Model Basin (Technical Report 1116), Feb. 1957.
%
% ------------------------------------ Contributers (in alphabetical order)
% Hsin-Lung Chung, Kathryn D'Epagnier, Brenden Epps,
% Dr. Justin Kerwin, Dr.Richard Kimball, M. Jordan Stanway, J. Mitch Stubblefield,
% Oscar Viquez R.
%
% =========================================================================
% =========================================================================
% ========================= Initiate OpenProp_v2.4.6 ========================
%
function OpenPropSingle
clear all;
clear global;
% warning off
addpath ../SourceCode
% addpath ./SourceCode
% ------------------------- Setup global variables ------------------------
global Fig_Main; % Main GUI figure
global Select;
global OpenPropDirectory SpecificationsValues DuctValues FlagValues FoilValues Filename...
XR_in XCoD_in XCD_in VAI_in VTI_in ri_in Xt0oD_in skew0_in rake0_in...
Meanline_cell Thickness_cell Values; % CavValues
% ------ Variable definitions ------
%
% Variables marked with ** are not taken from user input through the GUI.
% Instead, these variables are computed through formulas or remain unused
% in this version of the GUI but are still present to allocate space for
% future use.
%
% %
% % global Filename % Filename prefix
% %
% %
% % global SpecificationsValues; % Contains the following variables:
% % % General variables
% % global Z_in; % Number of blades
% % global N_in; % Propeller speed [RPM]
% % global D_in; % Propeller diameter [m]
% % global T_in; % Required thrust [N]
% % global Vs_in; % Ship speed [m/s]
% % global Dhub_in; % Hub diameter [m]
% %
% % global Js_in; % ** Js = Vs/(n*D) , advance coefficient
% % global KT_in; % ** KT = THRUST/(rho*n^2*D^4)
% % global n_in; % ** propeller speed [rev/s] = Vs/(Js*D) = N/60
% % % Advanced variables
% % global rho_in; % Water density
% % global Mp_in; % Number of vortex panels over the radius
% % global Np_in; % Number of points over the chord
% % global ITER_in; % Max iterations
% % global Rhv_in; % Hub vortex radius/hub radius
% % global SpecificationsText;
% %
% %
% % global DuctValues; % Contains the following variables:
% % % Ducted Propeller variables
% % global TAU; % Thrust ratio
% % global CDd; % Duct section drag coefficient
% %
% %
% % global CavValues; % Contains the following variables:
% % % Cavitation Analysis variables
% % global H_in; % Shaft centerline depth [m]
% % global dV_in; % Inflow variation [m/s]
% %
% %
% % global FlagValues; % Contains the following variables:
% % % Flags
% % global Propeller_flag; % 0 == turbine, 1 == propeller
% % global Hub_flag; % 0 == no hub, 1 == hub
% % global Duct_flag; % 0 == no duct, 1 == duct
% %
% % global Chord_flag; % ** CHORD OPTIMIZATION FLAG **
% %
% % global Viscous_flag; % 0 == viscous forces off (CD = 0), 1 == viscous forces on
% % global Plot_flag; % 0 == do not display plots, 1 == display plots
% %
% % global Camber_flag; % ** VERIFY USE, ADD TO GUI **
% %
% %
% % global FoilValues; % Contains the following variables:
% % % Airfoil type
% % global Meanline; % Meanline form
% % global Thickness; % Thickness form
% %
% % % Variables for geometry input table
% % global XR_in; % Radius ratio (r/R) at control point
% % global XCoD_in; % Camber to diameter ratio at XR
% % global XCD_in; % Coefficient of drag at XR
% % global VAI_in; % Va/Vs (wake profile at XR)
% % global VTI_in; % Vt/Vs (wake profile at XR)
% % global Xt0oD_in; % Thickness to camber ratio at XR
% % global skew0_in; % Skew at XR
% % global rake0_in; % Rake at XR
global N_R0; % Number of input radii
global Col_Label;
global XCoD_values XCLmax_values XCD_values;
% --- Set GUI element variables as global ---
% =========================================================================
% =========================================================================
% ========================== Initiate Main Figure =========================
Meanline_cell = {'NACA a=0.8' 'NACA a=0.8 (modified)' 'Parabolic'};
Thickness_cell = {'NACA 65A010' 'NACA 65A010 (modified)' 'Elliptical' 'Parabolic'};
% -------------------- Declare Default Input Variables --------------------
% Variables for geometry input table
XR_def = [.2 .3 .4 .5 .6 .7 .8 .9 .95 1]; % Radius ratio (r/R) at control point
N_R0 = length(XR_def); % Number of input radii
XCoD_def = [0.1600 0.1818 0.2024 0.2196 0.2305...
0.2311 0.2173 0.1806 0.1387 0.0010]; % chord to diameter ratio at XR
XCD_def = ones(1,N_R0).*0.008; % Coefficient of drag at XR
% VAI_def = ones(1,N_R0); % Va/Vs (wake profile at XR)
% VTI_def = zeros(1,N_R0); % Vt/Vs (wake profile at XR)
% f0oc_def = [0.0174 0.0195 0.0192 0.0175 0.0158 ...
% 0.0143 0.0133 0.0125 0.0115 0.0000];
t0oc0_def = [0.2056 0.1551 0.1181 0.0902 0.0694 ...
0.0541 0.0419 0.0332 0.0324 0.0100]; % Thickness to chord ratio at XR
Xt0oD_def = t0oc0_def .* XCoD_def;
skew0_def = zeros(N_R0); % Skew at XR
rake0_def = zeros(N_R0); % Rake at XR
XCLmax_def = 0.5 + (0.2-0.5)*(XR_def-XR_def(1))/(XR_def(end)-XR_def(1)); % CLmax distribution
% --- Set defaults for change callbacks ---
XCoD_values = XCoD_def;
XCLmax_values = XCLmax_def;
XCD_values = XCD_def;
% -----------------------------------------
% General variables
Z_def = 3; % Number of blades
N_def = 200; % Propeller speed [RPM]
D_def = 2; % Propeller diameter [m]
T_def = 40000; % Required thrust [N]
Vs_def = 5; % Ship speed [m/s]
Dhub_def = 0.4; % Hub diameter [m]
% Advanced variables
rho_def
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SourceCode.rar_lifting line_openprop_propeller_升力线_螺旋桨
共57个文件
m:49个
m~:6个
mat:1个
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收藏 174KB RAR 举报
温馨提示
采用升力线方法对螺旋桨进行性能计算并基于此进行螺旋桨的设计
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SourceCode.rar (57个子文件)
SourceCode
Induced_Velocity.m 1KB
VLMbucket.m 4KB
Analyze.m 42KB
VLM2D.m 10KB
colors.mat 399B
CLCD_vs_ALPHA.m 9KB
colors.m 4KB
Prop_usage_script.m 1KB
AnalyzeAuto.m~ 40KB
Make_ParReports.m 3KB
EppsOptimizer.m~ 48KB
Wake_Geometry.m 10KB
fig.m 139B
Make_Reports.m 18KB
ductVelocity.m 9KB
Wrench.m 3KB
Cav_PlotCP.m 576B
RepairSpline.m 4KB
OpenPropAnalyze.m 25KB
LerbsOptimizer.m 12KB
AnalyzeAuto.m 41KB
PlotMultipleFigures.m 3KB
OpenPropParam.m~ 52KB
Find_dHIFdBetaIC.m 1KB
clr.m 27B
Wake_Influence.m 5KB
Prop_usage_script.m~ 1KB
ductPlot.m 5KB
.DS_Store 15KB
ductThrust.m 3KB
References.m 4KB
Align_wake.m 4KB
EppsOptimizer.m 48KB
Prop_parinput.m 8KB
Find_tan_BetaI.m 802B
OpenPropSingle.m 96KB
Find_dUSTARdG.m 931B
Geometry.m 53KB
openprop.m 28B
elliptic12.m 5KB
OpenPropParam.m 52KB
OpenPropSingle.m~ 97KB
EppsParametricDucted.m 4KB
Wake_Horseshoe.m 4KB
LerbsParametric.m 14KB
Repair.m 4KB
Cav_CavitationMap.m 7KB
Make_Reports.m~ 18KB
Horseshoe.m 3KB
Forces.m 3KB
EppsParametric.m 4KB
ductInfluence.m 8KB
Bspline_basis.m 8KB
Find_dCLCDdALPHA.m 780B
GeometryFoil2D.m 11KB
InterpolateChord.m 13KB
Prop_input.m 10KB
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