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app.py

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+import gradio as gr
+import math
+
+# --- Data and Functions from your takeoff_model.py ---
+# I've copied all the calculation logic directly into this file
+# to make it a self-contained application.
+
+# Data Digitized from the PA-28-181 Chart
+TAKEOFF_DATA = {
+    0:    {8.283945422852682: 892.4445513013161, 29.982568972771546: 1283.66893069664},
+    1000: {-3.8119853338943273: 888.693875097673, 30.775981246618983: 1507.1707639598485},
+    2000: {-12.181282683176057: 892.3002945242533, 30.905812345975832: 1674.6528821301918},
+    3000: {-22.421109575043573: 882.9236040151468, 31.045260563803566: 1854.5410831279678},
+    4000: {-29.855142153032396: 893.021578409569, 30.908216625593553: 2077.7544028370503},
+    5000: {-37.61856103864879: 878.2112159644166, 30.775981246618983: 2307.1707639598485},
+}
+REFERENCE_WEIGHT_LBS = 2550.0
+MIN_CHART_WEIGHT_LBS = 2050.0
+
+def _interpolate_1d(x, x_points, y_points):
+    if x <= x_points[0]: return y_points[0]
+    if x >= x_points[-1]: return y_points[-1]
+    for i in range(len(x_points) - 1):
+        if x_points[i] <= x <= x_points[i+1]:
+            x1, x2 = x_points[i], x_points[i+1]
+            y1, y2 = y_points[i], y_points[i+1]
+            return y1 + (y2 - y1) * ((x - x1) / (x2 - x1))
+    return y_points[0]
+
+def _get_distance_at_temp_and_alt(temp, alt, data):
+    alt_points = sorted(data.keys())
+    alt_low, alt_high = -1, -1
+    if alt <= alt_points[0]: alt_low = alt_high = alt_points[0]
+    elif alt >= alt_points[-1]: alt_low = alt_high = alt_points[-1]
+    else:
+        for i in range(len(alt_points) - 1):
+            if alt_points[i] <= alt <= alt_points[i+1]:
+                alt_low, alt_high = alt_points[i], alt_points[i+1]
+                break
+    temp_points_low = sorted(data[alt_low].keys())
+    dist_points_low = [data[alt_low][t] for t in temp_points_low]
+    dist_at_alt_low = _interpolate_1d(temp, temp_points_low, dist_points_low)
+    if alt_low == alt_high: return dist_at_alt_low
+    temp_points_high = sorted(data[alt_high].keys())
+    dist_points_high = [data[alt_high][t] for t in temp_points_high]
+    dist_at_alt_high = _interpolate_1d(temp, temp_points_high, dist_points_high)
+    return _interpolate_1d(alt, [alt_low, alt_high], [dist_at_alt_low, dist_at_alt_high])
+
+def _calculate_weight_correction(base_distance, weight_lbs):
+    if weight_lbs >= REFERENCE_WEIGHT_LBS:
+        return 0.0
+    x_points = [1999.6411139821994, 2544.621494879893]
+    y_points = [840.3100775193798, 1410.8527131782948]
+    distance_at_actual_weight = _interpolate_1d(weight_lbs, x_points, y_points)
+    distance_at_reference_weight = _interpolate_1d(REFERENCE_WEIGHT_LBS, x_points, y_points)
+    weight_correction_delta = distance_at_actual_weight - distance_at_reference_weight
+    return weight_correction_delta
+
+def _calculate_headwind_correction(wind_knots):
+    # This function calculates the wind correction delta for HEADWIND.
+    x_points = [0.16104294478526526, 15.04722311914756]
+    y_points = [1139.2960929932183, 847.9173393606702]
+    distance_at_actual_wind = _interpolate_1d(wind_knots, x_points, y_points)
+    distance_at_zero_wind = _interpolate_1d(0, x_points, y_points)
+    wind_correction_delta = distance_at_actual_wind - distance_at_zero_wind
+    return wind_correction_delta
+
+def _calculate_tailwind_correction(wind_knots):
+    # This function calculates the wind correction delta for TAILWIND.
+    x_points = [0.16104294478526526, 5.268404907975452]
+    y_points = [1139.2960929932183, 1414.1427187600893]
+    distance_at_actual_wind = _interpolate_1d(wind_knots, x_points, y_points)
+    distance_at_zero_wind = _interpolate_1d(0, x_points, y_points)
+    wind_correction_delta = distance_at_actual_wind - distance_at_zero_wind
+    return wind_correction_delta
+
+def calculate_density_altitude(pressure_altitude_ft, outside_air_temp_c):
+    """
+    Calculates density altitude based on pressure altitude and outside air temperature.
+    """
+    # Step 1: Calculate the ISA standard temperature at the given pressure altitude.
+    isa_temp_c = 15 - (2 * (pressure_altitude_ft / 1000))
+
+    # Step 2: Calculate the density altitude using the standard formula.
+    density_altitude_ft = pressure_altitude_ft + (120 * (outside_air_temp_c - isa_temp_c))
+
+    return density_altitude_ft
+
+def calculate_takeoff_roll(indicated_altitude_ft, qnh_hpa, temperature_c, weight_kg, wind_type, wind_speed, safety_factor):
+    # This function now returns all intermediate steps for display in the GUI.
+
+    # Step 0: Convert aircraft mass from kg to lbs for internal calculations
+    weight_lbs = weight_kg * 2.20462
+
+    # Step 1: Calculate Pressure Altitude from Indicated Altitude and QNH
+    pressure_altitude = indicated_altitude_ft + ((1013.2 - qnh_hpa) * 27)
+    
+    # Step 2: Calculate Density Altitude
+    density_altitude = calculate_density_altitude(pressure_altitude, temperature_c)
+
+    base_distance = _get_distance_at_temp_and_alt(temperature_c, pressure_altitude, TAKEOFF_DATA)
+    weight_delta = _calculate_weight_correction(base_distance, weight_lbs)
+    distance_after_weight = base_distance + weight_delta
+    
+    wind_delta = 0.0
+    if wind_type == "Headwind":
+        wind_delta = _calculate_headwind_correction(wind_speed)
+    elif wind_type == "Tailwind":
+        wind_delta = _calculate_tailwind_correction(wind_speed)
+        
+    distance_after_wind = distance_after_weight + wind_delta
+    
+    # Apply the safety factor
+    final_distance_ft = distance_after_wind * safety_factor
+    final_distance_m = final_distance_ft * 0.3048 # Conversion factor for feet to meters
+    
+    return (
+        f"{pressure_altitude:.0f} ft",
+        f"{density_altitude:.0f} ft",
+        f"{base_distance:.1f} ft",
+        f"{weight_delta:.1f} ft",
+        f"{distance_after_weight:.1f} ft",
+        f"{wind_delta:.1f} ft",
+        f"{final_distance_ft:.0f} ft\n{final_distance_m:.0f} m"
+    )
+
+# --- Custom CSS for Styling the Columns ---
+# This CSS will style the textboxes within the columns that have the specific classes.
+custom_css = """
+.orange-column .gradio-textbox { background-color: #FFF5E1 !important; border-color: #F39C12 !important; }
+.orange-column .gradio-textbox > label > span { color: #E67E22 !important; }
+.green-column .gradio-textbox { background-color: #E8F8F5 !important; border-color: #2ECC71 !important; }
+.green-column .gradio-textbox > label > span { color: #1E8449 !important; }
+.green-column textarea { font-size: 1.2em !important; font-weight: bold !important; text-align: center !important; }
+"""
+
+# --- Gradio Interface Definition ---
+with gr.Blocks(theme=gr.themes.Soft(), css=custom_css) as demo:
+    gr.Markdown(
+        """
+        # PA-28-181 Takeoff Ground Roll Calculator
+        Enter the conditions below to calculate the takeoff distance.
+        """
+    )
+    
+    with gr.Row():
+        # Column 1: Inputs
+        with gr.Column(scale=2):
+            altitude = gr.Slider(minimum=0, maximum=8000, value=2000, step=50, label="Indicated Altitude (ft)")
+            qnh = gr.Slider(minimum=950, maximum=1050, value=1013.2, step=0.1, label="QNH (hPa)")
+            temp = gr.Slider(minimum=-40, maximum=40, value=21, step=1, label="Outside Air Temp (°C)")
+            weight = gr.Slider(minimum=930, maximum=1160, value=1090, step=5, label="Aircraft Mass (kg)")
+            wind_type = gr.Radio(["Headwind", "Tailwind"], label="Wind Type", value="Headwind")
+            wind_speed = gr.Slider(minimum=0, maximum=20, value=8, step=1, label="Wind Speed (knots)")
+            safety_factor = gr.Slider(minimum=1.0, maximum=2.0, value=1.0, step=0.05, label="Safety Factor")
+
+        # Column 2: Intermediate Computations (Orange)
+        with gr.Column(scale=2, elem_classes="orange-column"):
+            pressure_alt_output = gr.Textbox(label="1. Calculated Pressure Altitude", interactive=False)
+            density_alt_output = gr.Textbox(label="2. Calculated Density Altitude", interactive=False)
+            base_dist_output = gr.Textbox(label="3. Base Distance (from Alt/Temp)", interactive=False)
+            weight_delta_output = gr.Textbox(label="4. Weight Correction Delta", interactive=False)
+            dist_after_weight_output = gr.Textbox(label="5. Distance After Weight Adj.", interactive=False)
+            wind_delta_output = gr.Textbox(label="6. Wind Correction Delta", interactive=False)
+        
+        # Column 3: Final Output (Green)
+        with gr.Column(scale=1, elem_classes="green-column"):
+            output_distance = gr.Textbox(label="Final Ground Roll", interactive=False, lines=2)
+
+    inputs = [altitude, qnh, temp, weight, wind_type, wind_speed, safety_factor]
+    outputs = [pressure_alt_output, density_alt_output, base_dist_output, weight_delta_output, dist_after_weight_output, wind_delta_output, output_distance]
+    
+    btn = gr.Button("Calculate", variant="primary")
+    btn.click(fn=calculate_takeoff_roll, inputs=inputs, outputs=outputs)

requirements.txt

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+gradio