buffalo_wings.airfoil.Naca45DigitModifiedThicknessClassic

class buffalo_wings.airfoil.Naca45DigitModifiedThicknessClassic(mti, lei, lmti)[source]

Bases: Thickness

Base class for the NACA modified 4-digit and 5-digit airfoil thickness.

The thickness is parameterized on the square root of the chord location where the thickness is desired. This is to remove singularities that occur at the leading edge for the typical chord length parameterization.

Parameters:

mti (float)
lei (float)
lmti (float)

__init__(mti, lei, lmti)[source]

Initialize a modified NACA thickness distribution.

Parameters:

mti (float) – Maximum-thickness index as a percent of chord.
lei (float) – Leading-edge shape index.
lmti (float) – Maximum-thickness-location index.

Raises:

ValueError – If any input index is outside the supported modified-series range.

Return type:

None

Methods

`__init__`(mti, lei, lmti)	Initialize a modified NACA thickness distribution.
`delta`(t)	Return the thickness at specified parameter location.
`delta_t`(t)	Return first derivative of thickness at specified parameter location.
`delta_tt`(t)	Return second derivative of thickness at specified parameter location.
`discontinuities`()	Return the locations of any discontinuities in the thickness.
`max_thickness_parameter`()	Return parameter coordinate of maximum thickness.

Attributes

`a`	Return the fore-section coefficients.
`d`	Return the aft-section coefficients.
`leading_edge_index`	Return the leading-edge index.
`loc_max_thickness_index`	Return the maximum-thickness-location index.
`max_thickness_index`	Return the maximum-thickness index.

property max_thickness_index: float

Return the maximum-thickness index.

Returns:: Maximum thickness as a percent-chord index.
Return type:: float

property leading_edge_index: float

Return the leading-edge index.

Returns:: Leading-edge shape index for the modified thickness relation.
Return type:: float

property loc_max_thickness_index: float

Return the maximum-thickness-location index.

Returns:: Index locating where the fore and aft relations meet.
Return type:: float

property a: ndarray[tuple[int, ...], dtype[float64]]

Return the fore-section coefficients.

Returns:: Coefficients for the fore-section thickness relation.
Return type:: buffalo_wings.type_aliases.FloatArray

property d: ndarray[tuple[int, ...], dtype[float64]]

Return the aft-section coefficients.

Returns:: Coefficients for the aft-section thickness relation.
Return type:: buffalo_wings.type_aliases.FloatArray

discontinuities()[source]

Return the locations of any discontinuities in the thickness.

Returns:: Parametric coordinates of any discontinuities.
Return type:: List[float]

max_thickness_parameter()[source]

Return parameter coordinate of maximum thickness.

Returns:: Parameter coordinate of maximum thickness.
Return type:: float

delta(t)[source]

Return the thickness at specified parameter location.

Parameters:: t (numpy.ndarray) – Parameter location of interest. Equal to the square root of the desired chord location.
Returns:: Thickness at specified parameter.
Return type:: numpy.ndarray

delta_t(t)[source]

Return first derivative of thickness at specified parameter location.

Parameters:: t (numpy.ndarray) – Parameter location of interest. Equal to the square root of the desired chord location.
Returns:: First derivative of thickness at specified parameter.
Return type:: numpy.ndarray

delta_tt(t)[source]

Return second derivative of thickness at specified parameter location.

Parameters:: t (numpy.ndarray) – Parameter location of interest. Equal to the square root of the desired chord location.
Returns:: Second derivative of thickness at specified parameter.
Return type:: numpy.ndarray