Subsonic Wind Tunnel Cruise Test Section
Provides continuous airspeed from 25 to 80 m/s with flow angularity < 0.1 degrees.
Aerospace & Aeronautical Engineering / Power Required & Cruise
FREE TO EXPLORELABORATORY 20 · AEROSPACE & AERONAUTICAL ENGINEERING
Steady Level Flight Performance and Power Required Curves
Determine minimum drag speed V_md, parasite vs induced drag crossover, and power required curves P_R(V) for an aircraft in steady unaccelerated level cruise. Explore interactive wind tunnel simulation, flight dynamics, and aerospace engineering telemetry.
AERODYNAMICS · PROPULSION · FLIGHT DYNAMICS
Your virtual aerospace engineering laboratory.
PARASITE THRUST REQUIRED—
FLIGHT & TEST CELL TELEMETRY
Ready to sample with q = 2.0 kPa.
Adjust q, then execute aerospace trial.
Aeronautical telemetry and flight states are evaluated rigorously using 64-bit IEEE 754 precision. Residuals reflect ordinary least-squares regression across successive observations. Continuous data structures support high-fidelity aerodynamic modeling.
Aeronautical assumptions and boundary condition limits
Assumes parabolic drag polar without Mach compressibility drag rise (valid for M < 0.65). Linear regression of parasite thrust against dynamic pressure yields an equivalent parasite area f = 0.4500 m^2 with R^2 > 0.999999.
Aeronautical apparatus & wind tunnel sensors.
Business Jet Scale Model (1:10 scale)
Complete aerodynamic configuration with wing area S = 18.0 m^2 equivalent and clean fuselage.
6-Component Internal Strain-Gauge Balance
Measures total axial drag and normal lift forces with 0.05% full-scale precision.
Computer-Controlled Pitch & Speed Synchronizer
Adjusts model pitch to ensure lift constantly matches simulated aircraft weight (L = W).
Precision Pitot-Static Dynamic Pressure Rake
Continuously measures test-section dynamic pressure q in kPa.
Flight Performance Simulation Workstation
Computes parasite thrust component, constructs power required curves, and determines V_md.
FOLLOW THE METHOD
A reason behind every step.
Determine minimum drag speed V_md, parasite vs induced drag crossover, and power required curves P_R(V) for an aircraft in steady unaccelerated level cruise. Standardized parameter settings: 0.6, 1.0, 1.5, 2.2, 3.0, 4.0 kPa.
01
Zero Tare and Weight Calibration
Perform wind-off balance tare across all load cells with the 1:10 scale business jet model mounted on the sting.
02
Level Flight Trim Initialization
Set simulated aircraft weight to W = 45.0 kN, programming the auto-trimmer to maintain L = W at all test velocities.
03
Dynamic Pressure Stepping
Step the wind tunnel dynamic pressure through q = 0.60, 1.00, 1.50, 2.20, 3.00, and 4.00 kPa.
04
Drag Force Acquisition
Sample balance drag force across 3000 points at each dynamic pressure setting, resolving total drag into D_0 and D_i.
05
Parasite Thrust Isolation
Subtract theoretical induced drag D_i = W^2 / (q * S * pi * e * AR) from total drag to isolate parasite thrust T_parasite.
06
Parasite Drag Area Regression
Plot T_parasite (in kN) versus q (in kPa), perform linear regression to determine equivalent parasite area f = S * C_D0, and calculate (L/D)_max.
YOUR NOTEBOOK · 0 OBSERVATIONS
Turn measurements into aerodynamic insight.
Points are your recorded observations. The solid regression line validates Power Required & Cruise mathematical scaling.
LINEAR REGRESSION FIT · y = mx + b
T_{\text{parasite}} = f \cdot q \implies T_{\text{parasite}} = m \cdot q_{\text{kPa}} + b
| # | Dynamic Pressure q (kPa) | Parasite Thrust Required (kN) | Dynamic Pressure q (kPa) | Parasite Thrust Required T_parasite (kN) | Remove |
|---|
No readings yet. Execute an aerodynamic trial and record it.
Calculate it yourself.
CHECK YOUR UNDERSTANDING