6x3.1SF (6x31SF.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.5000 -0.2174 0.0000 0.0000 0.2500 0.0000 0.1255 0.0000 0.0627 0.0000 0.0450 0.0000 0.0000 0.0580 0.4914 0.1499 0.0053 -0.0627 0.2468 0.0035 0.1179 0.8325 0.0580 0.0393 0.0473 0.0011 -0.0001 0.1160 0.4790 0.4891 0.0405 -0.1183 0.2434 0.0131 0.1110 3.1793 0.0532 0.0429 0.0535 0.0043 -0.0002 0.1740 0.4658 0.8012 0.1309 -0.1218 0.2401 0.0271 0.1046 6.8266 0.0487 0.0436 0.0609 0.0092 0.0006 0.2320 0.4548 1.0874 0.2962 -0.0214 0.2373 0.0441 0.0987 11.4848 0.0449 0.0410 0.0694 0.0155 0.0025 0.2900 0.4487 1.3488 0.5476 0.2160 0.2354 0.0626 0.0934 16.7283 0.0419 0.0362 0.0800 0.0226 0.0054 0.3480 0.4490 1.5866 0.8834 0.6014 0.2348 0.0813 0.0885 21.9998 0.0397 0.0305 0.0925 0.0301 0.0090 0.4060 0.4555 1.8018 1.2826 1.0871 0.2357 0.0987 0.0841 26.6924 0.0383 0.0248 0.1058 0.0376 0.0134 0.4640 0.4673 1.9955 1.7011 1.6040 0.2386 0.1133 0.0801 30.2627 0.0374 0.0197 0.1180 0.0447 0.0182 0.5220 0.4825 2.1690 2.0732 2.0583 0.2437 0.1238 0.0766 32.2975 0.0370 0.0160 0.1273 0.0507 0.0231 0.5800 0.4997 2.3233 2.3224 2.3463 0.2515 0.1288 0.0735 32.5082 0.0367 0.0142 0.1320 0.0539 0.0264 0.6390 0.5173 2.4616 2.4616 2.4972 0.2608 0.1296 0.0706 31.5147 0.0365 0.0140 0.1330 0.0540 0.0279 0.7143 0.5370 2.6131 2.6131 2.6578 0.2712 0.1300 0.0676 30.2099 0.0363 0.0139 0.1338 0.0538 0.0297 0.7906 0.5537 2.7399 2.7399 2.7871 0.2801 0.1296 0.0650 28.8812 0.0360 0.0141 0.1338 0.0536 0.0315 0.8668 0.5673 2.8426 2.8426 2.8901 0.2875 0.1285 0.0630 27.5606 0.0357 0.0144 0.1332 0.0531 0.0334 0.9431 0.5780 2.9236 2.9236 2.9715 0.2932 0.1268 0.0614 26.2606 0.0355 0.0146 0.1320 0.0524 0.0353 1.0194 0.5860 2.9856 2.9856 3.0339 0.2975 0.1245 0.0602 24.9918 0.0353 0.0148 0.1301 0.0515 0.0372 1.0957 0.5913 3.0310 3.0310 3.0797 0.3004 0.1215 0.0594 23.7632 0.0351 0.0148 0.1277 0.0503 0.0388 1.1719 0.5941 3.0625 3.0625 3.1118 0.3019 0.1180 0.0589 22.5828 0.0350 0.0149 0.1248 0.0490 0.0401 1.2482 0.5945 3.0826 3.0826 3.1326 0.3020 0.1140 0.0586 21.4575 0.0348 0.0148 0.1213 0.0476 0.0410 1.3245 0.5927 3.0939 3.0939 3.1448 0.3009 0.1095 0.0585 20.3936 0.0347 0.0147 0.1173 0.0460 0.0414 1.4008 0.5888 3.0988 3.0988 3.1509 0.2985 0.1045 0.0585 19.3965 0.0345 0.0145 0.1129 0.0441 0.0414 1.4770 0.5830 3.1000 3.1000 3.1536 0.2949 0.0992 0.0585 18.4712 0.0341 0.0142 0.1081 0.0420 0.0407 1.5533 0.5754 3.1000 3.1000 3.1555 0.2902 0.0935 0.0586 17.6215 0.0337 0.0139 0.1029 0.0396 0.0394 1.6296 0.5661 3.1000 3.1000 3.1577 0.2844 0.0874 0.0586 16.8444 0.0332 0.0135 0.0973 0.0369 0.0375 1.7059 0.5552 3.1000 3.1000 3.1604 0.2775 0.0811 0.0586 16.1313 0.0325 0.0130 0.0914 0.0339 0.0350 1.7821 0.5430 3.1000 3.1000 3.1634 0.2697 0.0745 0.0586 15.4746 0.0318 0.0125 0.0851 0.0305 0.0321 1.8584 0.5295 3.1000 3.1000 3.1670 0.2609 0.0677 0.0587 14.8682 0.0311 0.0119 0.0786 0.0268 0.0287 1.9347 0.5149 3.1000 3.1000 3.1711 0.2512 0.0607 0.0587 14.3065 0.0302 0.0113 0.0719 0.0227 0.0249 2.0110 0.4994 3.1000 3.1000 3.1757 0.2407 0.0536 0.0587 13.7849 0.0293 0.0106 0.0649 0.0182 0.0207 2.0872 0.4830 3.1000 3.1000 3.1811 0.2293 0.0464 0.0587 13.2994 0.0284 0.0100 0.0577 0.0133 0.0162 2.1635 0.4658 3.1000 3.1000 3.1871 0.2173 0.0390 0.0587 12.8464 0.0274 0.0093 0.0504 0.0080 0.0114 2.2398 0.4482 3.1000 3.1000 3.1935 0.2045 0.0316 0.0588 12.4227 0.0263 0.0087 0.0430 0.0023 0.0064 2.3161 0.4301 3.1000 3.1000 3.2009 0.1911 0.0242 0.0588 12.0257 0.0253 0.0080 0.0355 -0.0039 0.0011 2.3923 0.4117 3.1000 3.1000 3.2092 0.1771 0.0167 0.0588 11.6529 0.0242 0.0074 0.0279 -0.0105 -0.0044 2.4686 0.3932 3.1000 3.1000 3.2186 0.1626 0.0092 0.0588 11.3023 0.0231 0.0068 0.0202 -0.0176 -0.0100 2.5449 0.3747 3.0983 3.0983 3.2274 0.1475 0.0018 0.0589 10.9661 0.0221 0.0062 0.0126 -0.0251 -0.0157 2.6212 0.3563 3.0881 3.0881 3.2283 0.1320 -0.0056 0.0589 10.6200 0.0210 0.0057 0.0049 -0.0331 -0.0214 2.6974 0.3382 3.0686 3.0686 3.2212 0.1161 -0.0130 0.0589 10.2625 0.0199 0.0052 -0.0027 -0.0416 -0.0272 2.7737 0.3200 3.0399 3.0399 3.2064 0.0994 -0.0203 0.0589 9.8943 0.0189 0.0047 -0.0102 -0.0509 -0.0330 2.8468 0.2884 3.0036 3.0036 3.1844 0.0686 -0.0297 0.0590 9.5322 0.0170 0.0038 -0.0203 -0.0677 -0.0404 2.8652 0.2765 2.9932 2.9932 3.1788 0.0568 -0.0327 0.0590 9.4400 0.0163 0.0035 -0.0236 -0.0741 -0.0428 2.8803 0.2652 2.9842 2.9842 3.1816 0.0456 -0.0354 0.0590 9.3634 0.0156 0.0032 -0.0266 -0.0804 -0.0449 2.8955 0.2522 2.9748 2.9748 3.1870 0.0327 -0.0383 0.0590 9.2865 0.0149 0.0030 -0.0299 -0.0876 -0.0473 2.9106 0.2373 2.9650 2.9650 3.1962 0.0179 -0.0415 0.0590 9.2092 0.0140 0.0026 -0.0335 -0.0958 -0.0499 2.9258 0.2201 2.9549 2.9549 3.2032 0.0006 -0.0451 0.0590 9.1316 0.0130 0.0023 -0.0376 -0.1058 -0.0531 2.9409 0.1997 2.9444 2.9444 3.2029 -0.0197 -0.0493 0.0590 9.0536 0.0118 0.0020 -0.0423 -0.1178 -0.0571 2.9561 0.1749 2.9335 2.9335 3.2052 -0.0445 -0.0542 0.0590 8.9753 0.0103 0.0017 -0.0479 -0.1321 -0.0617 2.9712 0.1425 2.9223 2.9223 3.2579 -0.0769 -0.0600 0.0590 8.8967 0.0084 0.0011 -0.0548 -0.1499 -0.0667 2.9864 0.0910 2.9107 2.9107 3.5304 -0.1281 -0.0686 0.0590 8.8177 0.0054 0.0005 -0.0653 -0.1768 -0.0735 3.0000 0.0136 2.9000 2.9027 2.9027 -0.2050 -0.0809 0.0590 8.7543 0.0008 0.0000 -0.0809 0.0000 0.0000 RADIUS: 3.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.58 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.005471 TOTAL WEIGHT (Kg) = 0.002481 TOTAL VOLUME (IN**3) = 0.089131 TOTAL PROJECTED AREA (IN**2) = 2.7162 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000023 MOMENT OF INERTIA (Kg-M**2) = 0.000003 STATIC MOMENT, ONE SIDE (IN-LB) = 0.002753 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 104.360 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 8795.75 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.91, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.00, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412