diff --git a/src/xfoilbasic.jl b/src/xfoilbasic.jl
index 3e81c7f..e95abd3 100644
--- a/src/xfoilbasic.jl
+++ b/src/xfoilbasic.jl
@@ -3,7 +3,7 @@
 Input x and y airfoil coordinates into XFOIL
 Coordinates must start at the trailing edge and loop counterclockwise.
 """
-function setCoordinates(x::Array{Float64,1},y::Array{Float64,1})
+function setCoordinates(x::AbstractArray{<:Real,1},y::AbstractArray{<:Real,1})
   if length(x) != length(y)
     error("x and y arrays must match in length")
   end
@@ -31,9 +31,9 @@ Run XFOIL's PANE Command (repanel airfoil)
 - `xpref1::Float64=1.0`: Bottom side refined area x/c limits
 - `xpref2::Float64=1.0`:
 """
-function pane(;npan::Integer=140,cvpar::Float64=1.0,cterat::Float64=0.15,
-  ctrrat::Float64=0.2,xsref1::Float64=1.0,xsref2::Float64=1.0,xpref1::Float64=1.0,
-  xpref2::Float64=1.0)
+function pane(;npan::Integer=140,cvpar::Real=1.0,cterat::Real=0.15,
+  ctrrat::Real=0.2,xsref1::Real=1.0,xsref2::Real=1.0,xpref1::Real=1.0,
+  xpref2::Real=1.0)
   xfoilglobals.npan[1] = npan
   xfoilglobals.cvpar[1] = cvpar
   xfoilglobals.cterat[1] = cterat
@@ -51,7 +51,7 @@ end
 Compute the flow solution at specified angle of attack (in degrees).
 Returns cl,cd,cdp,cm,converged
 """
-function solveAlpha(angle::Float64,re::Float64;mach::Float64=0.0,iter::Integer=50)
+function solveAlpha(angle::Real,re::Real;mach::Real=0.0,iter::Integer=50)
   cl = zeros(Float64,1)
   cd = zeros(Float64,1)
   cdp = zeros(Float64,1)
diff --git a/src/xfoilsweep.jl b/src/xfoilsweep.jl
index 1db4cf3..73cd574 100644
--- a/src/xfoilsweep.jl
+++ b/src/xfoilsweep.jl
@@ -3,11 +3,11 @@
 Performs angle of attack sweep using Xfoil.  A number of options are available
 to improve convergence and customize the run. Returns cl,cd,cdp,cm,converged
 # Arguments
-- `x::Array{Float64,1}`: Airfoil coordinates start from trailing edge looping counterclockwise
-- `y::Array{Float64,1}`:
-- `aoa::Array{Float64,1}`: Array of angle of attacks in degrees
-- `re::Float64`: Reynolds number
-- `ma::Float64`: Mach number
+- `x::AbstractArray{<:Real,1}`: Airfoil coordinates start from trailing edge looping counterclockwise
+- `y::AbstractArray{<:Real,1}`:
+- `aoa::AbstractArray{<:Real,1}`: Array of angle of attacks in degrees
+- `re::Real`: Reynolds number
+- `ma::Real`: Mach number
 - `iter::Integer=50`: Maximum number of iterations
 - `npan::Integer=140`: Number of panels
 - `percussive_maintenance::Bool=true`: Try harder to achieve convergence
@@ -16,8 +16,9 @@ to improve convergence and customize the run. Returns cl,cd,cdp,cm,converged
 - `clmaxstop::Bool=false`: Stop if lift coefficient decreases twice consecutively going up
 - `clminstop::Bool=false`: Stop if lift coefficient increases twice consecutively going down
 """
-function xfoilsweep(x::Array{Float64,1},y::Array{Float64,1},aoa::Array{Float64,1},
-  re::Float64;mach::Float64=0.0,iter::Integer=50,
+function xfoilsweep(x::AbstractArray{<:Real,1},y::AbstractArray{<:Real,1},
+  aoa::AbstractArray{<:Real,1},
+  re::Real;mach::Real=0.0,iter::Integer=50,
   npan::Integer=140,percussive_maintenance::Bool=true,printdata::Bool=false,
   zeroinit::Bool=true,clmaxstop::Bool=false,clminstop::Bool=false)
 
@@ -47,8 +48,8 @@ function xfoilsweep(x::Array{Float64,1},y::Array{Float64,1},aoa::Array{Float64,1
   return cl,cd,cdp,cm,conv
 end
 
-function xfoilsweep(x::Array{Float64,1},y::Array{Float64,1},aoa::Array{Float64,1},
-  re::Float64,mach::Float64,iter::Integer,
+function xfoilsweep(x::AbstractArray{<:Real,1},y::AbstractArray{<:Real,1},aoa::AbstractArray{<:Real,1},
+  re::Real,mach::Real,iter::Integer,
   npan::Integer,percussive_maintenance::Bool,printdata::Bool,
   clmaxstop::Bool,clminstop::Bool)
 
@@ -110,8 +111,8 @@ end
 Attempts to converge previously unconverged XFOIL solutions through modifying the
 solution initial conditions. Returns cl,cd,cdp,cm,converged
 """
-function dopercussivemaintainance(x::Array{Float64,1},y::Array{Float64,1},
-  aoa::Float64,re::Float64,mach::Float64,iter::Integer,npan::Integer)
+function dopercussivemaintainance(x::AbstractArray{<:Real,1},y::AbstractArray{<:Real,1},
+  aoa::Real,re::Real,mach::Real,iter::Integer,npan::Integer)
   remod = re
   aoamod = aoa
   for j = 1:25