diff --git a/aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_aero_buildup/fuselage_transonics.py b/aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_aero_buildup/fuselage_transonics.py
index c6dbef96..5a678a73 100644
--- a/aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_aero_buildup/fuselage_transonics.py
+++ b/aerosandbox/aerodynamics/aero_3D/test_aero_3D/test_aero_buildup/fuselage_transonics.py
@@ -33,6 +33,6 @@
 ).run()
 
 plt.plot(op_point.mach(), aero["CD"], zorder=1.9, label="Model without Wave Drag")
-p.show_plot("Transonic Fuselage Drag", "Mach [-]", "Drag Area $C_D \cdot A$ [m$^2$]")
+p.show_plot("Transonic Fuselage Drag", "Mach [-]", r"Drag Area $C_D \cdot A$ [m$^2$]")
 
 print("%.4g" % aero["CD"][-1])
diff --git a/aerosandbox/library/aerodynamics/unsteady.py b/aerosandbox/library/aerodynamics/unsteady.py
index 489e3c30..c19fdda8 100644
--- a/aerosandbox/library/aerodynamics/unsteady.py
+++ b/aerosandbox/library/aerodynamics/unsteady.py
@@ -435,6 +435,6 @@ def linear_ramp_pitch(reduced_time: float) -> float:
     plt.plot(reduced_time, added_mass_lift, label="Added Mass Lift", lw=2)
     plt.legend()
     plt.xlabel("Reduced time")
-    plt.ylabel("$C_\ell$")
+    plt.ylabel(r"$C_\ell$")
     plt.title("Guassian Pitch Maneuver Through Top-Hat Gust")
     plt.show()
diff --git a/aerosandbox/library/gust_pitch_control.py b/aerosandbox/library/gust_pitch_control.py
index f84a9dfd..5434e4d8 100644
--- a/aerosandbox/library/gust_pitch_control.py
+++ b/aerosandbox/library/gust_pitch_control.py
@@ -142,7 +142,7 @@ def calculate_transients(self):
     ax1.legend(loc="lower left")
     ax2.legend(loc="lower right")
     ax1.set_xlabel("Reduced time")
-    ax1.set_ylabel("$C_\ell$")
+    ax1.set_ylabel(r"$C_\ell$")
     ax2.set_ylabel("Angle of attack, degrees")
     plt.title("Optimal Pitch Maneuver Through Top-Hat Gust")
     plt.show()
diff --git a/aerosandbox/library/power_turboshaft.py b/aerosandbox/library/power_turboshaft.py
index 65ca6e05..6fab5053 100644
--- a/aerosandbox/library/power_turboshaft.py
+++ b/aerosandbox/library/power_turboshaft.py
@@ -158,7 +158,7 @@ def thermal_efficiency_turboshaft(
     p.show_plot(
         "Turboshaft: Thermal Efficiency at Partial Power",
         "Throttle Setting [-]",
-        "Thermal Efficiency Knockdown relative to Design Point [-] $\eta / \eta_\mathrm{max}$",
+        r"Thermal Efficiency Knockdown relative to Design Point [-] $\eta / \eta_\mathrm{max}$",
     )
 
     ##### Do Weight/OPR Efficiency Plot #####
diff --git a/aerosandbox/modeling/splines/hermite.py b/aerosandbox/modeling/splines/hermite.py
index c053a781..8bd2bd2b 100644
--- a/aerosandbox/modeling/splines/hermite.py
+++ b/aerosandbox/modeling/splines/hermite.py
@@ -80,12 +80,12 @@ def cosine_hermite_patch(
     dfdx_b: float,
     extrapolation: str = "continue",
 ) -> Union[float, np.ndarray]:
-    """
+    r"""
     Computes a Hermite patch (i.e., values + derivatives at endpoints) that uses a cosine function to blend between
     linear segments.
 
     The end result is conceptually similar to a cubic Hermite patch, but computation is faster and the patch is
-    C^\infty-continuous.
+    $C^\infty$-continuous.
 
     Args:
         x: Scalar or array of values at which to evaluate the patch.
diff --git a/aerosandbox/structures/tube_spar_bending.py b/aerosandbox/structures/tube_spar_bending.py
index c6064e7b..cdd86cba 100644
--- a/aerosandbox/structures/tube_spar_bending.py
+++ b/aerosandbox/structures/tube_spar_bending.py
@@ -340,7 +340,7 @@ def draw(self, show=True):
             # "Local Slope [deg]": np.arctan2d(self.du, 1),
             "Local Load [N/m]": self.distributed_force,
             "Axial Stress [MPa]": self.stress_axial / 1e6,
-            "Bending $EI$ [N $\cdot$ m$^2$]": self.elastic_modulus * self.I,
+            r"Bending $EI$ [N $\cdot$ m$^2$]": self.elastic_modulus * self.I,
             "Tube Diameter [m]": self.diameter,
             "Wall Thickness [m]": self.wall_thickness,
         }