From a0ebaa8419c92fd906fc9133aa4dc11674c51f0b Mon Sep 17 00:00:00 2001
From: Benjamin Crews <aceF22@gmail.com>
Date: Tue, 14 May 2024 22:03:29 -0400
Subject: [PATCH] Version attribute and fuselage fix.

Added __version__ to the package init instead of package main.

Fixed the Fuselage.Cover.panel_flutter dynamic pressure. Pressures are provided in thousands of feet.
---
 src/hyperstruct/__init__.py |  4 ++++
 src/hyperstruct/fuselage.py | 12 +++++++++---
 2 files changed, 13 insertions(+), 3 deletions(-)

diff --git a/src/hyperstruct/__init__.py b/src/hyperstruct/__init__.py
index 6d456bf..378c206 100644
--- a/src/hyperstruct/__init__.py
+++ b/src/hyperstruct/__init__.py
@@ -1,6 +1,10 @@
 """Hyperstruct."""
 
 from dataclasses import dataclass
+from importlib.metadata import version
+
+
+__version__ = version("hyperstruct")
 
 
 @dataclass
diff --git a/src/hyperstruct/fuselage.py b/src/hyperstruct/fuselage.py
index 3df23f5..159197b 100644
--- a/src/hyperstruct/fuselage.py
+++ b/src/hyperstruct/fuselage.py
@@ -255,22 +255,28 @@ def panel_flutter(self, mach: float, altitude: float) -> float:
         To find the final required thickness, this method must be looped
         over for all Mach and altitudes corresponding to the flight
         envelope conditions of the aircraft.
+
+        Inputs: Mach Number, and Altitude (in thousands of feet)
+        Returns: Field Thickness
         """
         # Dynamic pressures based on standard day atmosphere.
         # Dynamic Pressure, q, in [psf]
         # Altitudes must be measured in [ft]
-        if altitude <= 20000:
+        if altitude <= 20:
             q = mach**2 * (1479.757 - 52.187 * altitude + 0.619868 * altitude**2)
-        elif 20000 < altitude <= 70000:
+        elif 20 < altitude <= 70:
             q = mach**2 * (
                 1465.175
                 - 50.76695 * altitude
                 + 0.6434412 * altitude**2
                 - 0.002907194 * altitude**3
             )
-        elif altitude > 70000:
+        elif altitude > 70:
             q = mach**2 * (199.659 / altitude) ** 4
 
+        # Dynamic pressure is in [psf] convert to [psi]
+        q = q / 144
+
         # Calculate the Mach Number Effect
         # The Mach Number Effect, FM, is a 3 piece function from SWEEP.
         # This function is more conservative than the AFRL baseline curve,