Aircraft Wing Taper Ratio wing tip chord Solver

            from math import *

def aircraft_wing_taper_ratio_solve_a(c, b) -> float:
    return (c * b)

assert abs(aircraft_wing_taper_ratio_solve_a(0.375, 4.8) - 1.7999999999999998) < 1e-6 * max(1.0, abs(1.7999999999999998))
          

            #include <assert.h>
#include <math.h>

double aircraft_wing_taper_ratio_solve_a(double c, double b) {
    return (c * b);
}

int main(void) {
    const double expected = 1.7999999999999998;
    const double actual = aircraft_wing_taper_ratio_solve_a(0.375, 4.8);
    assert(fabs(actual - expected) < 1e-6 * fmax(1.0, fabs(expected)));
}
          

            #include <cassert>
#include <cmath>
#include <numbers>

double aircraft_wing_taper_ratio_solve_a(double c, double b) {
    return (c * b);
}

int main() {
    constexpr double expected = 1.7999999999999998;
    const double actual = aircraft_wing_taper_ratio_solve_a(0.375, 4.8);
    assert(std::fabs(actual - expected) < 1e-6 * std::fmax(1.0, std::fabs(expected)));
}
          

x86-64 NASM · System V ABI · Linux · SSE2 with libm where required

            ; double aircraft_wing_taper_ratio_solve_a(double c, double b)
; Linux x86-64 NASM · System V ABI · first eight doubles in xmm0–xmm7
global aircraft_wing_taper_ratio_solve_a
section .text

aircraft_wing_taper_ratio_solve_a:
    push rbp
    mov rbp, rsp
    sub rsp, 32
    movsd [rbp-8], xmm0
    movsd [rbp-16], xmm1
    movsd xmm0, [rbp-8]
    mulsd xmm0, [rbp-16]
    movsd [rbp-24], xmm0
    movsd xmm0, [rbp-24]
    leave
    ret
          

            function result = aircraft_wing_taper_ratio_solve_a(c, b)
    result = (c * b);
end
          

            ClearAll[mwCalculate];
mwCalculate[c_, b_] := (c * b);