From 990b13051c7606337a057cabeaa7c917e710dda4 Mon Sep 17 00:00:00 2001
From: Maurice Zimmnau <zimmnau@ilr.rwth-aachen.de>
Date: Thu, 20 Feb 2025 14:39:01 +0100
Subject: [PATCH] Apply 1 suggestion(s) to 1 file(s)
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Co-authored-by: Florian Schültke <florian.schueltke@ilr.rwth-aachen.de>
---
aerodynamic_analysis/src/methods/liftingLinePolar.cpp | 2 +-
1 file changed, 1 insertion(+), 1 deletion(-)
diff --git a/aerodynamic_analysis/src/methods/liftingLinePolar.cpp b/aerodynamic_analysis/src/methods/liftingLinePolar.cpp
index 8231e7ea..cd6bfd83 100644
--- a/aerodynamic_analysis/src/methods/liftingLinePolar.cpp
+++ b/aerodynamic_analysis/src/methods/liftingLinePolar.cpp
@@ -248,7 +248,7 @@ double liftingLinePolar::getCLmax_clean(double Mach) {
// (small) influence of sweep -> assumption delta y ~ 2.1
double CLmax2Clmax_phiLE0 = 0.9; // [Ray18] Fig. 12.8
double CLmax2Clmax_phiLE60 = 0.8; // [Ray18] Fig. 12.8
- double CLmax2Clmax_phiLE = CLmax2Clmax_phiLE0 + (CLmax2Clmax_phiLE60 - CLmax2Clmax_phiLE0) / (cos(convertDegree(RADIAN, 60)) - 1.) * (cos(phi_LE_rad) - 1.); // [Ray18] Fig. 12.8
+ double CLmax2Clmax_phiLE = CLmax2Clmax_phiLE0 + (CLmax2Clmax_phiLE60 - CLmax2Clmax_phiLE0) / (cos(convertUnit(DEGREE, RADIAN, 60)) - 1.) * (cos(phi_LE_rad) - 1.); // [Ray18] Fig. 12.8
double CLmax_inc = CLmax2Clmax_phiLE * Clmax_sec;
// Decrease due to Mach number
double delta_CLmax_Ma06 = -0.2 * cos(phi_LE_rad); // according to [Ray18] Fig. 12.9 (not exact, but influence neglectable --> not too big)
--
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