#include <stdio.h>
#include <stdlib.h>

#include <assert.h>

#include "atragmx.h"

int main(int argc, char** argv) {
	ATragMXSolution *result = NULL;

	ATragMXContext ctx = {
		.atmosphere = {
			.atmosphere_model = ICAO,
			.barometric_pressure = 1096.0,
			.relative_humidity = 50.0,
			.temperature = 15.2,
			.wind_dir = 4,
			.wind_speed = { 2.3, 2.7 }
		},
		.gun = {
			.air_friction = 0.0,
			.ballistic_coef = 0.4,
			.bore_height = 0.08,
			.bullet_mass = 10.0,
			.drag_model = DRAG_G1,
			.muzzle_velocity = 850.0,
			.scope_angle = 0.0,
			.twist_dir = 1,
		},
		.target = {
			.speed = 5.5,
			.direction = 5,
			.inclination_angle = 12.3,
			.latitude = 45.0,
			.range = 625.0,
		},
		.sim_steps = 100,
		.stability_factor = 1,
		.store_range_card = true,
	};

    ace_ballistics ctx_ace_ballistics = {
		.enabled = true,
    };
	ace_config ctx_ace = {
		.ballistics = &ctx_ace_ballistics,
	};

	result = ATragMXCalcSolution(&ctx, &ctx_ace);

	if (!result) {
		perror("Calculation failed");
		exit(EXIT_FAILURE);
	}

    printf("=== Solution ===\n");
    printf("Elevation (radians): %.6f\n", result->elev);
    printf("Windage W1: %.6f, W2: %.6f\n", result->windage.w1, result->windage.w2);
    printf("Lead: %.6f\n", result->lead);
    printf("Time of flight: %.4f s\n", result->time_of_flight);
    printf("Remaining velocity: %.2f m/s\n", result->remaining_velocity);
    printf("Remaining energy: %.2f J\n", result->remaining_energy);
    printf("Coriolis vertical drift: %.6f\n", result->coriolis_vdrift);
    printf("Coriolis horizontal drift: %.6f\n", result->coriolis_hdrift);
    printf("Spin drift: %.6f\n", result->spin_drift);

    assert(ctx.store_range_card);

    assert(result->range_card != NULL);

    if (ctx.store_range_card && result->range_card != NULL) {
        printf("\nRange card (sim_steps = %zu):\n", ctx.sim_steps);
        for (size_t i = 0; i < ctx.sim_steps; i++) {
            printf("  step %3zu: %.3f\n", i, (result->range_card->card+i)->kinetic_energy);
        }
    }

	exit(EXIT_SUCCESS);
}