diff --git a/functions/odeFunctions/ballistic.m b/functions/odeFunctions/ballistic.m
index 505fc2cf4aa6678e685c420d484c5ecf6ad9101b..586d36b069df7c1ab511c9842b5a2c8845f541c7 100644
--- a/functions/odeFunctions/ballistic.m
+++ b/functions/odeFunctions/ballistic.m
@@ -149,7 +149,7 @@ betaOut = beta;
 
 %% INTERPOLATE AERODYNAMIC COEFFICIENTS:
 
-if abs(alpha)>25*pi/180 || abs(beta)>25*pi/180 && altitude < environment.effectiveRampAltitude
+if abs(rad2deg(alpha))>25*pi/180 || abs(rad2deg(beta))>25*pi/180
     coeffsValues = interpN( rocket.coefficientsHighAOA.total,...
         {rocket.coefficientsHighAOA.state.alphas, rocket.coefficientsHighAOA.state.machs, ...
         rocket.coefficientsHighAOA.state.betas, rocket.coefficientsHighAOA.state.altitudes}, ...
diff --git a/functions/simulations/stdStability.m b/functions/simulations/stdStability.m
index be527860a6f4086684210f31a8c9ea105606dcc4..969c9fc5b56eeb841d9a9e03ea65da60d973f84a 100644
--- a/functions/simulations/stdStability.m
+++ b/functions/simulations/stdStability.m
@@ -61,8 +61,8 @@ mach = stability.interp.mach(end);
 xcg = interpLinear(rocket.motor.time, rocket.xCg, tPad);
 
 %%% create dissileMatcom input data struct
-dissileVars.alpha = sort([-alpha, alpha, 0, -1, 1]);
-dissileVars.beta = beta;
+dissileVars.alpha = sort([-rad2deg(alpha), rad2deg(alpha), 0, -1, 1]);
+dissileVars.beta = rad2deg(beta);
 dissileVars.alt = alt;
 dissileVars.mach = mach;
 dissileVars.xcg = xcg;