S1223 airfoil disadvantages. You have 0 S1223 airfoil how to# S1223 airfoil code# The shape is not perfectly similar especially in the lower surface, since it is more difficult to be approximated. 000000 0. The research findings from the structural analysis of the S1223 high-lift airfoil indicated that it is applicable for use in an unmanned aerial vehicle as well as a novel reciprocating-airfoil-driven vertical take-off and landing (VTOL) drone model. 926390 0. II. 104120 0. 673600 0. 1. The maximum coefficient of drag is 0. Enes Coskun. 14% to 8. Mazz. The airfoils that employ Stratford distribution (Liebeck) for pressure recovery are not the most suitable solution for motorsports efficiency because of the amendments in the trailing edge radii of these two airfoils, ranging from 0. The dat file is in Selig format. May 22, 2012 · CFD Analysis of Aerodynamic Characteristics of Low Reynold’s Number High Lift Airfoils FX 63-137 and Selig S1223 by deploying Gurney Flaps. 1) and the 3D sketch of wing model is prepared in Solidwork is shown in Fig. ) 10 pF. To simulate the GH19 airfoil with the same tools and in the same conditions of the S1223 analysis; 3. 8%c and a maximum camber of 8. With vortex generators and a 1% chord Gurney ap (used separately), the Cl,max increased to 2. 7 % and straight on the bottom side www. Ta=25 ℃, Typ. The contour of airfoil S1223 is shown in Fig. Based on the outcome of the Xfoil results, the best three airfoils i. The UIUC [35] experimental data give a maximum lift coefficient of approximately 2. 980750 0. The angle of attack was varied and their effect was seen on velocity, pressure, coefficient of lift and coefficient of drag. March 31st, 2016. 30. Keywords: CFRP, finite element analysis, high-lift, S1223, strain, stress, VTOL. Polar details for airfoil (aerofoil)S1223(s1223-il) Xfoil prediction at Reynolds number 50,000 and Ncrit 9. Results at different Reynolds and AOA The CFD analysis on the S1223 airfoil have been repeated at Re = 2e04 and 2e05. Perform computational fluid dynamics flow Jan 3, 2021 · Aranake et al. 958840 0. The S1223 airfoil has 11. 080440 0. LaSalle exchange of S1223 to S1223RTL grow to be finished. You have 0 Jul 30, 2017 · The airfoils sections used for spoilers in the current study are NACA0012, NACA4412, and S1223. 80%, while the camber is decreased from 8. Selig S1223 high lift low Reynolds number airfoil. The Be 122 series looks about right, you might want to then thicken them up using Excel. 004940 0. 109350 0. So the system has tendency to bring Oct 8, 2022 · In this experiment, a NACA 4412 wing test section was analyzed for its aerodynamic coefficient performance at low Reynolds numbers using a sting balance and data acquisition system. The S1223 airfoil gives maximum lift coefficient within the given range of Reynolds Apr 13, 2023 · The potential of airfoil optimisation for the specific requirements of airborne wind energy (AWE) systems is investigated. 2. 016460 0. Hence E423 aerofoil is considered for the present study. An airfoil is a thin curved slice whose pressure distribution depends on its velocity and position in relation to the motion of the air around it. 97) at Re =55,000 and 148,000 through xfoil code The present paper includes CFD analysis of the isolated wings of the Airbus A380 during take-off, cruise and landing modes, the model development has been performed using the GAMBIT 2. Nov 14, 2021 · The low Reynolds number S1223 airfoil, considered as a reference airfoil and investigated in this research work, has a maximum thickness of 12. It was determined that S1223 aerofoil creates a high lift at the expense of an increase in drag. S1223 airfoil, produces the second highest amount of lift coefficient that can be seen in the table 4 and figure 4. 25% to 1. Experimental results were found for airfoil S1223 that had been tested in the University of Illinois at Urbana-Champaign (UIUC) subsonic wind tunnel[5]. So what I might recommend doing is making your front wing entirely out of NACA 6412 of 4412 profiles, and to use them for your rear wing flaps as well. Here, Fluent fluid flow analysis was simulated for 500 RPM and 1000 RPM momentum injection with free stream velocities from 5 m/s to 30 m/s for different angles of attack of 0 to 20 degrees. 50% (till 1. 46% at the maximum camber position of 49%. 00%), Selig S1223 airfoil would be efficient whereas at higher trailing edge radius (more roundness), that is, above 0. View in full-text Context 2 S1223 Airfoil. That is the reason why all modern gliders and most modern GA designs use laminar airfoils. Therefore, selecting the right airfoil is a critical aspect of wind turbine design and optimization as it affects the amount of power generated by the turbine. 041160 0. Selig and Guglielmo [7] followed the footprints of Eppler and designed airfoil S1223 (Fig. 1%c located at 18. 54), ANSYS-Fluent (Version 2021 R2), and SOLIDWORKS Simulation (Version 2022 R1). It is located at 25% of the chord length from the leading edge of the airfoil. 1% at 49% chord. 8% at 30. 988250 0. The UIUC Airfoil Data Site gives some background on the database. S1223 RTL. May 30, 2022 · Results are also reported at Re = 2e04 and Re = 2. 994170 0. e. 2 with moderate stall characteristics as shown in Fig. Dat file. Clark developed the profile in 1922. May 28, 2019 · In short, while the S1223 does have amazing lift characteristics (at lower Reynolds numbers -- these trends may not hold to a Reynolds number of 3,000,000, which would be closer to an operating sailplane), it is actually not the right airfoil for a regular sailplane. It can be concluded that, till the roundness of the trailing edge of 0. Fig3. 91 and 1. One study proposed embedding a rotating cylinder onto the Selig S1223 airfoil to test its aerodynamic performance for high altitude platform (HAP) purposes. the airfoil has a 13. It has a maximum thickness of 12. 001260 0. Journal of Applied Fluid Mechanics (JAFM), 9 (2), 537-542. Feb 21, 2024 · The original airfoil S1223 and the new airfoil S1223 modified are compared to observe the differences in lift coefficient and drag ratio: The variation of the lift coefficient of the two airfoils to the angle of attack is plotted in Fig. 5 and polar curve for airfoil S1223 is shown in Fig. Max camber 10. 20 but for further increment of mach number lift coefficient keep decreasing up to the value of mach number 0. To compare the performance of both airfoils, assessing the advantages and disadvantages of the GH19 airfoil in comparison to the S1223; and 4. The main original aspect of this numerical research has been the sensitivity analysis of the aerodynamic performance of the S1223 airfoil over a wide range of Reynolds number. The velocity (and thus pressure) distribution at the suction side of the airfoil close to the leading edge was modified employing full inverse method, which utilizes Lighthill and Van Ingen complex mapping method. The airfoil first appeared in UIUC LSATs Vol 1 without pitching Feb 26, 2024 · The results show that the new airfoil exhibits a 7% higher lift, 5. from the structural analysis of the S1223 high-lift airfoil indicated that it is applicable for use in an unmanned aerial vehicle as. 028530 0. This airfoil exclusively designed and used for low Reynolds number applications [8]. 637980 0. S1223, a low Reynolds number high lift airfoil, is suitable for short-field aircraft operations S1223 - Selig S1223 high lift low Reynolds number airfoil. Richard T. 114250 0. 074020 0. Airfoil Tools Search 1638 airfoils Tweet. Perform computational fluid dynamics flow Wortmann FX 63-137 and Selig S1223 are high lift low Reynolds Number Airfoils which have widespread applications in heavy lift cargo planes and student projects like FSAE. The diameter of the airfoil is 11. Abstract - This paper presents investigation on airfoil S1223, S819, S8037 and S1223 RTL at low speeds to find out the most suitable airfoil design to be used in the low speed aircrafts. This work presents a numerical analysis of the ability of the high lift airfoil profile Selig S1223 for working as hydrofoil under water conditions. Plot and print the shape of an airfoil (aerofoil) for your specific chord width and transformation. Answers to frequently asked questions are posted here Aug 25, 2016 · Selig S1223 airfoil with 25cm chord and 3m span By Autodesk Inventor with export as STL file Polar details for airfoil (aerofoil)S1223 RTL(s1223rtl-il) Xfoil prediction at Reynolds number 1,000,000 and Ncrit 9 Aug 14, 2018 · The samples of aerodynamic coefficients for the S1223 airfoil are generated by the optimal Latin hypercube design method. 022500 0. 1%c located at 49%c. Source UIUC Airfoil Coordinates Database. 1% at 19. LaSalle modification of the S1223 to S1223RTL. 2% of chord. Oct 1, 2017 · Wortmann FX 63-137 and Selig S1223 are high lift low Reynolds Number Airfoils which have widespread applications in heavy lift cargo planes and student projects like FSAE. Show abstract. Sep 16, 2022 · Usability of the Selig S1223 Profile Airfoil as a High Lift Hydrofoil for Hydrokinetic Application The numerical analysis carried out shows the advantages and disadvantages of a few turbulence Clark Y airfoil Pros and Cons. In wind-tunnel tests, the new airfoil yielded a maximum lift coef cient of 2. 2% at 49. Improving Airfoil Drag Prediction. , Photosensitivity: λ=780 nm, Dark current: V R =20 V, Cutoff frequency: V R =20 V, Terminal capacitance: V R =20 V, f=1 MHz, Noise equivalent power: V R =20 V, λ=λp, unless otherwise noted. efficient whereas at higher trailing edge radius (more Jul 1, 2009 · They added that these models will output good results at high Reynolds number; however, Ma and Liu [22] used SA model to simulate aerodynamic characteristics of S1223 airfoil and showed that the Yes, the S1223 airfoil has a recommended wing spar location. pdf), Text File (. Feb 24, 2022 · The research findings. Table 1 shows some performance data of the S1223 and Figure 8a is a plot of the S1223 lift coefficient (CL ) versus the AoA as a fixed airfoil, which indicates that the maximum airfoil coefficient of lift at a Reynolds number of 2 ×105 , is approximately 2. 098590 0. 02790 (at radius of 1. Open full The selected S1223 profile belongs to the high lift low Reynolds profiles class (Selig and Guglielmo 1997) (see Fig. com S1223 airfoils are widely used. The optimum airfoil has the higher camber by comparison with the initial airfoil. Noise equivalent power (typ. The S1223 airfoil model The value of lift coefficient for S1223 RTL airfoil keep increasing from mach number of 0. 564650 0. This paper studies the variation in lift coefficients, drag coefficients and aerodynamic efficiency because of the amendments in the UIUC Airfoil Coordinates Database. The optimised geometry was generated using the NSGA-II optimisation algorithm in conjunction with 2D-RANS simulations. Parser. 28 X 10 . 50% of chord) and minimum The 2D sketch of wing model is plotted in airfoil plotter (refer to Fig. 859470 0. 23 [16]. Aerodynamic comparison concluded S1223 as the most dominating airfoil based on Lift Force and CH 10 as the The Selig's S1223 airfoil wing was investigated for the taper ratio, created in CATIA V5 and analyzed in ANSYS. The results shown below are preliminary and subject to change upon final data reduction. The analysis showed a 39% enhancement in lift coefficient and a 53% delay in stall angle for the modified airfoil compared to the unmodified model. well as a novel reciprocating-airfoil airfoils which are supposed to have high lift-drag ratio at cruising attack angle along with a good property of stall characteristics. 527440 0. 16 for the design of the computational model which includes the design of the isolated wings of the Airbus A380 that uses a blend of NASA SC(2)_0610 and NASA SC Polar details for airfoil (aerofoil)S1223(s1223-il) Xfoil prediction at Reynolds number 1,000,000 and Ncrit 9 In order to verify the rationality of the numerical simulation, the aerodynamic performance data of the numerical simulation are compared with the experimental data of airfoil S1223 with the relative thickness of 12. Download scientific diagram | Lift and Drag forces for s1223 airfoil at angle of attack 0. 25mm. S1223 exhibits high lift characteristics whereas, the NACA 9315 displays low drag coefficient [16]. S1223 airfoil is 0. This contrast can be attributed to the more pronounced curvature along the centerline (camber line) of the S1223 airfoil, setting it apart from the S809 airfoil. ***** Dec 7, 2005 ***** The S1223 airfoil which has been used in the SAE AeroDesign Competition has been retested at UIUC to obtain the pitching moment data. This paper presents investigation on airfoil S1223, S819, S8037 and S1223 RTL at low speeds to find out the most suitable airfoil design to be used in the low speed aircrafts. 010370 0. Airfoil modification The S1223 airfoil leading edge radius is increased by 20% and blended at 10% distance from the leading edge. Polar details for airfoil (aerofoil)S1223 RTL(s1223rtl-il) Xfoil prediction at Reynolds number 200,000 and Ncrit 5 stall angle-of-attack increases on the both airfoils. from publication: Computational Fluid Dynamic Analysis of Flapping Wing of Micro Aerial Vehicle at Very Sep 23, 2022 · Usability of the Selig S1223 pro le airfoil as a high lift hydrofoil for hydrokinetic application. The S1223 was chosen due to its superb ability to generate lift at low Reynolds numbers. Reynolds amount for the simulations modified into Re=2. 601580 0. In wind-tunnel tests, the new airfoil yielded a maximum lift coefficient of 2. The modified trailing edge of the S1123 profile was analyzed in Investigation on airfoil S 1223, S819, S8037 and S1223 RTL at low speeds to find out the most suitable airfoils design to be used in the low speed aircrafts is presented. txt) or read online for free. 0 × 10 5. Airfoil polar at Re = 2e05, CFD Vs Experimental data 3. 9% chord. 8% chord. 832770 0. 804120 0. The document summarizes a student group's report on building a mock-up of an airfoil and identifying its key parts and movements. (The Reynolds number relates the inertial forces to the viscous forces of a fluid in motion. Khan et al. Terminal capacitance (typ. (s1223rtl-il) S1223 RTL. (ch10sm-il) CH10 (smoothed) Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil. S1223. The S1223RTL airfoil is asymmetrical. , including lift and drag analysis, and Figure 2. 773690 0. 6. 708230 0. Disadvantages. Polar details for airfoil (aerofoil)S1223(s1223-il) Xfoil prediction at Reynolds number 200,000 and Ncrit 9. The shape of an airfoil influences its lift, drag, stability, and control Aug 4, 2021 · Thin section airfoils are aptly considered to progress. Another study analyzed the The S1223 & NACA 9315 airfoil designs have been mentioned in several studies [14] [15][16]. The airfoil shape used on this aircraft was the Selig S1223. 943890 0. 6 (a) and (b). 3. Max thickness 13. Experimental and numerical investigations were conducted at high Reynolds numbers for the S1223 airfoil and an optimised airfoil with thin slat. Fig. Absar A. S1223 is an airfoil used in heavy lift cargo planes [2]. compared NACA0006, E423, S1223 and FX 74-CL4-14 aerofoils for wind turbine enclosure application. 034760 0. 3. The results indicate that, If there is no sweep angle, dihedral, or polyhedral angle Polar details for airfoil (aerofoil)S1223(s1223-il) Xfoil prediction at Reynolds number 50,000 and Ncrit 5. The method used for analysis of airfoils is Jan 1, 2020 · The S1223 RTL airfoil has been chosen as the most suitable design for the specified boundary conditions and the Mach number from 0. 8% chord, a maximum camber of 8. Measurement condition. 5. 10 to 0. 4: Performance curves of S1223 obtained from XFLGR/XFOIL for various Reynolds number and Mach 0. The shape of an aircraft's airfoil can affect its efficiency, handling characteristics, and range. The results indicate that the Nov 1, 2017 · It ca n be concluded that, till the roundness of the trailing edge of 0. It can be represented mathematically as, XFOIL is widely-used, in academia and parts of industry for quick preliminary estimates of airfoil performance due to its ease of use and versatility [6] Aerodynamic performance comparison of S1223 airfoil between experimental data and XFOIL, performed by Wei Shyy et. With vortex generators and a 1 % chord Gurney flap (used separately), the C l,max increased Based on the outcome of the Xfoil results, the best three airfoils i. The Wopt The Selig S1223 airfoil has been modified for various purposes. Khan and Wasif Mirza Saeed Three codes for airfoil design and analysis (PROFOIL, the Eppler code, and ISES) were used to design the example S1223 high-lift airfoil for a Reynolds number of 2 × 10 5. It was just scaled and extruded. five% max thickness at 19. 047680 0. 50% of chord (starting from 0. The method used for analysis of airfoils is Computational Fluid Dynamics (CFD). 1), which has the highest maximum lift coefficient among all the airfoils that are presented here. Aug 6, 2021 · Laminar airfoil pros: Low drag at an intermediate AoA range. 50% of chord). Specifically, the airfoil thickness is reduced from 12. three% at fifty 5. To model a NACA 4412airfoil and S1223 airfoils. The dat file data can either be loaded from the airfoil database or your own airfoils which can be entered here and they will appear in the list of airfoils in the form below. Apr 21, 2023 · Víctor Hugo Gomez Gonzalez, Carlos Artemio Macias Rodas, Pascual López de Paz, Orlando Lastres Danguillecourt, Guillermo Ibañez Duharte; Analysis of s834, s1223 and eppler 420 airfoil geometries for a hydrokinetic turbine. 3). The paper is having a hierarchical multi-objective optimization on the basis of the high-lift airfoil S1223 by combing direct search optimization algorithm EXTREM and airfoil flow field solver Aug 5, 2021 · The gap between the airfoil and the wall represents the variable of the research parameter, h/c. It focuses on the S1223 airfoil profile, describing its maximum thickness, camber, chord length, and performance The S1223 airfoil model has a chord of 150mm and a span of 506. The Selig (S1223-il) airfoil has been used in Nov 6, 2021 · Semantic Scholar extracted view of "CFD Analysis of Aerodynamic Characteristics of Low Reynold’s Number High Lift Airfoils FX 63-137 and Selig S1223 by deploying Gurney Flaps. Lift characteristics for a Reynolds number of are shown in Fig. 87% to 8. (s1223-il) S1223. Clark Y is the term used for a specific airfoil profile, extensively being used in aircraft design elements for general purposes, and thoroughly investigated over the years in aerodynamics. The comparison of the lift coefficient curves is reported in Fig. 50% of chord), Wortmann FX 63-137 airfoil would be efficient. E423 aerofoil produces lesser lift and less drag compared to S1223 aerofoil. Literature shows that NACA 4412 and S1223 are one of the most commonly used airfoils for spoilers to This paper describes the methodology used to analyse oscillations of foils of a wide range of aspect ratios, 0. 2% higher sliding ratio than the base foil, and a 46% lower coefficient of moment than the base foil. 13%, which prove the n u m e r i c a l simulation of low-Reynolds-number and high-lift airfoil S1223 is reasonable. 884060 0. s1223 1. The analysis has resulted in a S1223 has very large lift to drag ratio for wide AoA and hence is suitable for low speed operation owing to its high camber (Fig 4). (starting from 0. Included below are coordinates for approximately 1,600 airfoils (Version 2. 4. The trailing edge is often given a radius for the ease of manufacturing and safety. 93% thickness and camber of 8. Jun 26, 2021 · This research focused on the structural design and analysis of a high-lift, low Reynolds number airfoil profile, the Selig S1223, under reciprocating inertial force loading, to determine the feasibility of its use in a new reciprocating airfoil (RA) driven VTOL UAV. 06 in terms of lift and coefficients, streamlines, pressure coefficient and velocity distributions, at 3 different AOA. Thanks go to Yvan Tinel for making the wind tunnel model. 4×10 -15 W/Hz 1/2. Under cambered airfoils, like S1223, have the best ratio of generating an extremely high lift at a minimum of flow velocity operation, and also this high lift is generated at very low angles of attack. 00%), Selig S1223 airfoil would be. For your rear wing mainplane, you'll want a bit of camber, so Benzing airfoils would be appropriate there. 97 respectively (at radius of 1. 4, where the black curve represents the optimized airfoil and the red curve represents the original airfoil. https://doi. Keywords: airfoil, trailing edge radius, high Lift, Selig S1223, wortmann FX 63-137, chord, computational fluid dynamics. 5% at the maximum thickness position of 19. The comparison was done on the basis coefficient of lift and coefficient of drag. The profile, S1223, was chosen after comparison with other profiles, due to its highest lift coefficient for Reynolds numbers between 2 105 and 3 105. 5% at 19. Source dat file. 5% of the chord length. You have 0 30 MHz. The original 1mm curve is included. Laminar airfoil cons: They work as intended only at Reynolds numbers between 1 Million and 5 Million - above that the transition happens very early, regardless of pressure distribution. 741660 0. 05 (20 m/s) This airfoil also has large value of negative moment coefficient. 906410 0. ) Because the wings have a short chord and the aircraft is flying Oct 30, 2023 · The majority of methods have forecasted a heightened turbulence level within the boundary layer of the S1223 airfoil in comparison to the S809 airfoil. 067490 0. Max thickness 12. An analysis performed on a 3D wing constructed with the new airfoil shows its applicability in constructing a light aircraft. Download files. Like. The RBF neural network is trained by these samples. 6% chord. OBJECTIVE The purpose of this study was to conduct computational fluid dynamics analysis of NACA 4412 and S1223 airfoils with below mentioned objectives. S1223 lift and pitching moment plots: The S1223 is a popular airfoil used in the SAE Aero Design Competition. The numerical simulation of low speed and high-lift airfoil has been done using Polar details for airfoil (aerofoil)S1223 RTL(s1223rtl-il) Xfoil prediction at Reynolds number 200,000 and Ncrit 9 S1223 aerofoil and the flat plate is proposed to test their aerodynamic performances for high altitude platform purposes. Figure 8 and 9 depicts the effect of differently located damages on Lift/Drag ratio at a wide range of angles-of-attack for the FX63-137 and S1223 airfoils respectively. ) 9. Airfoil report s1223 (1) - Free download as PDF File (. 5 ≤ AR ≤ 4, and Reynolds numbers, 10 ⁴ ≤ Re ≤ 10 ⁵ , for energy Dat file. The AF300 airfoil was optimized from existing low Re airfoils, initially taking S1210 and S1223 as base airfoil, and modifying by percentage increase in the trailing edge thickness, S1210 (3%) variant is selected based on its aerodynamic performance lift coefficient values close to 2 (1. However, the exact wing spar location may vary depending on the specific design and requirements of the aircraft. The Reynolds number ranges from 3. 50% of chord. You have 0 Polar details for airfoil (aerofoil)S1223(s1223-il) Xfoil prediction at Reynolds number 200,000 and Ncrit 5. Selig [35] to achieve a C l max greater than 2 at Re = 2. 3% at 55. Three codes for airfoil design and analysis (PROFOIL, the Eppler code, and ISES) were used to design the example S1223 high-lift airfoil for a Reynolds number of 2 3 105. 0). arpnjournals. 2% chord. It is clearly visible that for the both airfoils L/D ratio of damaged airfoils in comparison to undamaged airfoils is Title: Computional investigation of the low speed S1223 airfoil with and without a gurney flap Author: Edward Tejnil Created Date: 2/14/2022 10:30:39 AM Download scientific diagram | Profile of S1223 airfoil with chord length of 1 m from publication: Evaluation of Seat to Head Transmissibility at Different Backrest Conditions During Whole Body Jan 1, 2023 · This research is carried out at Reynolds number 300,000 on a test specimen wing with a Wing-span of 200 cm and a Wing-chord of 30 cm using XFLR-5 (version 6. 67%. Sep 16, 2022 · safety reasons), further improvements on the S1223 wing profile were made to implement it in a Formula Student race car [9]. The airfoil has approximately 10% more lift than the S1223. The S1223 airfoil is optimized to obtain the maximum lift-drag ratio by GA. Virginius E. FX63137sm, S1223, and e423 are chosen for understanding the aerodynamic characteristics. 060890 0. 086710 0. INTRODUCTION High lift airfoils like Wortmann FX 63-137 and S1223 is an airfoil used in heavy lift cargo planes [2]. 16xE5, equal with the reliable experimental facts from the design of the blade airfoil sections, which work together to produce lift and reduce drag. al. The geometry of the hydrofoil blade is designed through a suitable airfoil profile and then studied carefully by means of Computational Fluid Dynamics (CFD) in order to check its hydrodynamic behavior, i. 054270 0. The test Parametric optimization methods are employed to simultaneously reduce the thickness and camber of the airfoil. 1% at 49% chord, and the S1223 airfoil profile is shown in Figure 2. The link above includes the coordinates (plus airfoil as a nurb curve) and performance predictions from XFOIL. " by Absar A. 0279 and 2. The mass of the blade with thin airfoils will also be less, which requires a less starting torque and is competent to thick airfoil blade sections. . The characteristics. 998380 0. The airfoils are listed alphabetically by the airfoil filename (which is usually close to the airfoil name). View. May 1, 2016 · The S1223 airfoil was designed by M. [7] concluded that, overall the The effects of fluid flow have been studied over the two airfoils 4412 and S1223 through computational fluid dynamics. Max camber 8. 9% chord and max camber of eight. 3% chord. 092770 0. Download : Download high-res Mar 31, 2016 · S1223 airfoil. 42 X 10 5 to 10. Wind turbine blades with S-1223 airfoil with the bionic modification are considered for the evaluation of suitability for micro-turbines. Feb 28, 2019 · Richard T. 971110 0. wp ek xf lr xp is ln tg os oa