* Tel.: #45-45-25-43-24; fax: #45-45-93-06-93.E-mail address: [email protected] (A. Filippone).Progress in Aerospace Sciences 36 (2000) 629}654Data and performances of selected aircraft and rotorcraftAntonio Filippone*Department of Energy Engineering, Technical University of Denmark, Building 404, DK-2800 Lyngby, DenmarkAbstractThe purpose of this article is to provide a synthetic and comparative view of selected aircraft and rotorcraft (nearly 300of them) from past and present. We report geometric characteristics of wings (wing span, areas, aspect-ratios, sweepangles, dihedral/anhedral angles, thickness ratios at root and tips, taper ratios) and rotor blades (type of rotor, diameter,number of blades, solidity, rpm, tip Mach numbers); aerodynamic data (drag coe$cients at zero lift, cruise and maximumabsolute glide ratio); performances (wing and disk loadings, maximum absolute Mach number, cruise Mach number,service ceiling, rate of climb, centrifugal acceleration limits, maximum take-o! weight, maximum payload, thrust-to-weight ratios). There are additional data on wing types, high-lift devices, noise levels at take-o! and landing. The data arepresented on tables for each aircraft class. A graphic analysis o!ers a comparative look at all types of data. Accuracylevels are provided wherever available.  2000 Elsevier Science Ltd. All rights reserved.Contents1. Introduction. . . . . . . . . . . . . . .................................... 6312. Reliability of the data ............................................ 6323. Aerodynamic data .............................................. 6323.1. Drag coe$cients . . .......................................... 6333.2. Lift}drag ratio. ............................................. 6353.3. Cruise Lift and high-lift performances . . . ............................. 6364. Selected performance data . . ....................................... 6374.1. Mach number . . ............................................ 6374.2. Normal acceleration limits . . . . . . . . . . . . . . ........................ 6374.3. Rate of climb . ............................................. 6384.4. Hover ceiling . . . ........................................... 6384.5. Maximum take-o! weight and other weights............................ 6384.6. Wing loading . . ............................................ 6384.7. Noise levels . . ............................................. 6385. Geometrical data . .............................................. 6395.1. Wing geometry . ............................................ 6395.2. Wing span . . .............................................. 6405.3. Aspect-ratios and shape parameters . . ............................... 6400376-0421/00/$ - see front matter  2000 Elsevier Science Ltd. All rights reserved.PII: S 0 3 7 6 - 0 4 2 1 ( 0 0 ) 0 0 0 1 1 - 7NomenclatureA wing area; rotor disk area (m)AR wing geometrical aspect-ratiob wing span (m)B main rotor'snumberofblades(rotorcraft)c wing/blade chord (m)C"drag coe$cientC*lift coe$cientC*maximum lift coe$cientCDskin friction coe$cientd rotor diameter (m)dtail rotor diameter (m)d equivalent wing span (m)D drag force (N)e wing e$ciency factorE maximum cargo rangeg> maximum normal acceleration, g-limith hovering ceiling, out of ground e!ect (m)k reduced frequencyl aircraft length, or length scale (m)¸ lift force (N)LE leading edge lineM Mach numbern normal load factorP*max power loading"MTOW/T (kg/kNfor jets; kg/kW for propellers)Pspeci"c excess power (m/s)QC quarter chord lineq dynamic pressure (kg ms\)R aircraft range (km)Re Reynolds numberR!rate of climb (m/min)t/c wing thickness ratio¹ take-o! thrust rating (kN), InternationalStandard Atmosphere (ISA)u aircraft's speed (km/h, or m/s);aircraft's stalling velocity with #apsdown (km/h)=/A max wing loading"MTOW/A (kg/m);also equivalent disk loadingZ service ceiling in sustained horizontal#ight (m); vertical coordinatea angle of attack (deg)b dihedral angle, if '0; anhedral if (0(deg)j taper ratio"c/cK wing sweep around LE or QC, as speci-"ed (deg)c angle of climb (deg)k advance ratioo air density (kg/m)p rotor solidityHQ maximum sustained rate of turn (deg/s)Subscripts/superscripts[]cruise conditions[]root[]tip[]at zero lift[]viscousAircraft wing specixcationsBWB blended wing bodyFSW forward swept wingSBW swept back wingVSW variable sweep (usually discrete posi-tions)D conventional delta wingD double delta wingRotorcraft specixcationsAT attack, anti-tank, anti-submarine, ad-vanced military vehicleC cargo, crane, heavy lift transport (usuallymilitary vehicle)GE civil/military general purpose vehicle(patrol, rescue, transport)LC light commercial vehicle (for a few pas-sengers and limited freight)UT military utility vehicle (troops, freight,mateH riel, support operations)TW twin or tandem rotor, utility vehicle withtwo rotor shaftsTR tilt rotor vehicleOther symbols and abbreviationsAoA angle of attackEPNdB e!ective perceived noise, measured in dBLERX leading-edge root extensionMTOW maximum take-o! weight (kg)OWE operating empty weight (kg)PAY payload (kg)P/O PAY/OWEP/W PAY/MTOWrpm rounds-per-minute (rotor speeds)V/STOL vertical/short take-o! and landingSSF single-slotted TE #apDSF double-slotted TE #apTSF triple-slotted TE #apSL single LE slatSLK LE Kruger slatUSB upper surface blowingVT vectored thrustAircraft designationAircraft and rotorcraft are identixed by company name (Antonov, Lockheed)#designation (An-124, F-117)#version(A, B); nickname (Ruslan, Raptor) is rarely used. In the graphics the company names are added only occasionally.Refer to the data base [1] for full information and data that for clarity are not labelled.630 A. Filippone / Progress in Aerospace Sciences 36 (2000) 629}6545.4. Wing sweep . . . . . . . . . . . . . . . . . .............................. 6405.5. Airfoil sections. . ............................................ 6415.6. Other geometrical characteristics . . . . . .............................. 6426. Comparative analysis . . . . . . . ..................................... 6426.1. Helicopters. . .............................................. 6426.2. Cargo aircraft . . . . . . . . . . . . . . . . . . . ........................... 6466.3. Fighter jets. . . . . . . . . ....................................... 6496.4. Subsonic commercial jets . . . . . . . . . . . . . . . ........................ 6517. Perspectives and conclusions .