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Aerospace and Mechanical Engineering
matlab_airfoil_toolbox
Commits
799726cf
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Commit
799726cf
authored
3 years ago
by
Thomas Lambert
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docs(readme): fix typos
parent
be031f9b
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README.md
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799726cf
...
@@ -186,7 +186,7 @@ same order. These arguments can be of two types:
...
@@ -186,7 +186,7 @@ same order. These arguments can be of two types:
Some functions then extend these inputs by using various optional arguments.
Some functions then extend these inputs by using various optional arguments.
### extendpolar
###
#
extendpolar
This function extends known $
`C_l`
$ and $
`C_d`
$ polars to the full range of
This function extends known $
`C_l`
$ and $
`C_d`
$ polars to the full range of
angle of attacks [-180; 180]. This is especially useful when studying rotors and
angle of attacks [-180; 180]. This is especially useful when studying rotors and
...
@@ -207,10 +207,10 @@ import af_tools.extendpolar
...
@@ -207,10 +207,10 @@ import af_tools.extendpolar
| 'method' |
`'Viterna'`
|
`'Viterna'`
|
| 'method' |
`'Viterna'`
|
`'Viterna'`
|
| 'limit' |
`'stall','limit'`
|
`'last'`
|
| 'limit' |
`'stall','limit'`
|
`'last'`
|
### plotpolars
###
#
plotpolars
Plots the following polars: $
`C_l-\alpha`
,
$
`C_d-\alpha`
$
Plots the following polars: $
`C_l-\alpha`
$
,
$
`C_d-\alpha`
$
,
$
`C_m-\alpha`
$
,
$
`C_l/C_d-\alpha`
,
$
`C_m-\alpha`
$
,
$
`C_l/C_d-\alpha`
$
,
$
`C_l-C_d`
$.
,
$
`C_l-C_d`
$.
```
matlab
```
matlab
...
@@ -220,7 +220,7 @@ plotpolars(Polar)
...
@@ -220,7 +220,7 @@ plotpolars(Polar)
plotpolars
(
alpha
,
cl
,
cd
,
cm
)
plotpolars
(
alpha
,
cl
,
cd
,
cm
)
```
```
### findstall
###
#
findstall
Finds the stall angle of attack and the associated $
`C_l`
$ and $
`C_d`
$.
Finds the stall angle of attack and the associated $
`C_l`
$ and $
`C_d`
$.
...
@@ -231,7 +231,7 @@ import af_tools.findstall
...
@@ -231,7 +231,7 @@ import af_tools.findstall
[
alpha_s
,
cl_s
,
cd_s
]
=
findstall
(
alpha
,
cl
,
cd
)
[
alpha_s
,
cl_s
,
cd_s
]
=
findstall
(
alpha
,
cl
,
cd
)
```
```
### findzerolift
###
#
findzerolift
Finds the zero-lift angle of attack and the associated $
`C_d`
$.
Finds the zero-lift angle of attack and the associated $
`C_d`
$.
...
@@ -242,7 +242,7 @@ import af_tools.findzerolift
...
@@ -242,7 +242,7 @@ import af_tools.findzerolift
[
alpha_zeroL
,
cd_zeroL
]
=
findzerolift
(
alpha
,
cl
,
cd
)
[
alpha_zeroL
,
cd_zeroL
]
=
findzerolift
(
alpha
,
cl
,
cd
)
```
```
### findcllinearrange
###
#
findcllinearrange
Finds the range of angles of attack for which the $
`C_l`
$ can be considered
Finds the range of angles of attack for which the $
`C_l`
$ can be considered
linear.
linear.
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