6x4E (6x4E.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 4.0000 0.0000 0.0000 0.2500 0.0000 0.1343 0.0000 0.0672 0.0000 0.0500 0.0000 0.0000 0.0726 0.4801 4.0000 0.0130 -0.1820 0.2465 0.0087 0.1320 1.6317 0.0634 0.0641 0.0574 0.0052 -0.0200 0.1452 0.4659 4.0000 0.0991 -0.3333 0.2432 0.0321 0.1298 6.2002 0.0605 0.0689 0.0761 0.0106 -0.0128 0.2178 0.4617 4.0000 0.3141 -0.3508 0.2403 0.0660 0.1277 12.9265 0.0589 0.0699 0.1013 0.0156 -0.0012 0.2904 0.4710 4.0000 0.6890 -0.1567 0.2378 0.1067 0.1257 20.6884 0.0592 0.0679 0.1321 0.0198 0.0142 0.3630 0.4938 4.0000 1.2239 0.2831 0.2358 0.1502 0.1238 28.2179 0.0611 0.0637 0.1671 0.0233 0.0326 0.4356 0.5264 4.0000 1.8832 0.9519 0.2343 0.1929 0.1220 34.5309 0.0642 0.0583 0.2035 0.0260 0.0530 0.5082 0.5627 4.0000 2.5972 1.7797 0.2334 0.2308 0.1204 39.1239 0.0677 0.0520 0.2373 0.0280 0.0744 0.5808 0.5955 4.0000 3.2669 2.6201 0.2333 0.2603 0.1188 41.8355 0.0708 0.0455 0.2644 0.0293 0.0953 0.6534 0.6187 4.0000 3.7749 3.3006 0.2338 0.2774 0.1174 42.5980 0.0726 0.0393 0.2806 0.0297 0.1134 0.7260 0.6275 4.0000 3.9980 3.6714 0.2352 0.2785 0.1160 41.2326 0.0728 0.0340 0.2817 0.0277 0.1252 0.7985 0.6252 4.0000 4.0000 3.7830 0.2368 0.2677 0.1148 38.5642 0.0718 0.0299 0.2715 0.0240 0.1296 0.8693 0.6202 4.0000 4.0000 3.8455 0.2379 0.2551 0.1136 36.2155 0.0705 0.0274 0.2598 0.0210 0.1287 0.9401 0.6141 4.0000 4.0000 3.8674 0.2384 0.2403 0.1125 34.1059 0.0691 0.0268 0.2467 0.0164 0.1214 1.0108 0.6076 4.0000 4.0000 3.8648 0.2385 0.2235 0.1113 32.2031 0.0676 0.0273 0.2322 0.0108 0.1096 1.0816 0.6006 4.0000 4.0000 3.8614 0.2380 0.2065 0.1102 30.4818 0.0662 0.0278 0.2175 0.0055 0.0969 1.1523 0.5931 4.0000 4.0000 3.8526 0.2371 0.1901 0.1090 28.9199 0.0647 0.0280 0.2031 0.0010 0.0850 1.2230 0.5852 4.0000 4.0000 3.8419 0.2357 0.1747 0.1078 27.4982 0.0631 0.0277 0.1890 -0.0022 0.0747 1.2938 0.5768 4.0000 4.0000 3.8351 0.2337 0.1603 0.1067 26.2003 0.0615 0.0269 0.1753 -0.0039 0.0662 1.3645 0.5679 4.0000 4.0000 3.8311 0.2314 0.1466 0.1055 25.0118 0.0599 0.0259 0.1619 -0.0046 0.0588 1.4352 0.5585 4.0000 4.0000 3.8270 0.2285 0.1333 0.1044 23.9203 0.0583 0.0248 0.1489 -0.0053 0.0512 1.5060 0.5487 4.0000 4.0000 3.8230 0.2253 0.1204 0.1032 22.9151 0.0566 0.0237 0.1362 -0.0060 0.0437 1.5767 0.5384 4.0000 4.0000 3.8189 0.2215 0.1078 0.1020 21.9870 0.0549 0.0227 0.1239 -0.0067 0.0362 1.6475 0.5276 4.0000 4.0000 3.8148 0.2174 0.0956 0.1009 21.1278 0.0532 0.0216 0.1119 -0.0075 0.0287 1.7182 0.5164 4.0000 4.0000 3.8107 0.2128 0.0839 0.0997 20.3305 0.0515 0.0205 0.1002 -0.0083 0.0214 1.7889 0.5047 4.0000 4.0000 3.8067 0.2077 0.0725 0.0986 19.5889 0.0497 0.0194 0.0888 -0.0092 0.0141 1.8597 0.4925 4.0000 4.0000 3.8019 0.2023 0.0615 0.0974 18.8976 0.0480 0.0183 0.0778 -0.0102 0.0070 1.9304 0.4799 4.0000 4.0000 3.7965 0.1965 0.0508 0.0962 18.2518 0.0462 0.0172 0.0670 -0.0113 0.0000 2.0011 0.4668 4.0000 4.0000 3.7912 0.1903 0.0406 0.0951 17.6473 0.0444 0.0162 0.0566 -0.0124 -0.0068 2.0719 0.4532 4.0000 4.0000 3.7859 0.1837 0.0307 0.0939 17.0804 0.0426 0.0151 0.0466 -0.0136 -0.0134 2.1426 0.4391 4.0000 4.0000 3.7809 0.1767 0.0212 0.0928 16.5478 0.0407 0.0140 0.0368 -0.0150 -0.0198 2.2134 0.4246 4.0000 4.0000 3.7760 0.1693 0.0121 0.0916 16.0466 0.0389 0.0130 0.0274 -0.0165 -0.0260 2.2841 0.4096 4.0000 4.0000 3.7710 0.1616 0.0034 0.0904 15.5741 0.0370 0.0120 0.0184 -0.0180 -0.0320 2.3548 0.3942 4.0000 4.0000 3.7662 0.1535 -0.0050 0.0893 15.1280 0.0352 0.0110 0.0096 -0.0197 -0.0377 2.4256 0.3783 4.0000 4.0000 3.7617 0.1450 -0.0130 0.0881 14.7062 0.0333 0.0100 0.0012 -0.0214 -0.0432 2.4963 0.3619 4.0000 4.0000 3.7572 0.1363 -0.0206 0.0870 14.3069 0.0315 0.0091 -0.0069 -0.0233 -0.0484 2.5670 0.3450 4.0000 4.0000 3.7528 0.1272 -0.0278 0.0858 13.9282 0.0296 0.0082 -0.0146 -0.0252 -0.0534 2.6378 0.3277 4.0000 4.0000 3.7488 0.1177 -0.0347 0.0846 13.5686 0.0277 0.0073 -0.0221 -0.0272 -0.0581 2.7085 0.3099 4.0000 4.0000 3.7446 0.1080 -0.0412 0.0835 13.2269 0.0259 0.0065 -0.0292 -0.0293 -0.0626 2.7793 0.2916 4.0000 4.0000 3.7409 0.0980 -0.0473 0.0823 12.9016 0.0240 0.0057 -0.0359 -0.0315 -0.0668 2.8471 0.2713 4.0000 4.0000 3.7373 0.0858 -0.0534 0.0812 12.6042 0.0220 0.0049 -0.0427 -0.0349 -0.0709 2.8652 0.2624 4.0000 4.0000 3.7364 0.0791 -0.0557 0.0809 12.5273 0.0212 0.0045 -0.0453 -0.0376 -0.0725 2.8803 0.2531 4.0000 4.0000 3.7361 0.0718 -0.0579 0.0807 12.4634 0.0204 0.0042 -0.0480 -0.0409 -0.0740 2.8955 0.2419 4.0000 4.0000 3.7371 0.0626 -0.0606 0.0804 12.4002 0.0195 0.0038 -0.0510 -0.0451 -0.0759 2.9106 0.2285 4.0000 4.0000 3.7388 0.0513 -0.0637 0.0802 12.3377 0.0183 0.0034 -0.0547 -0.0506 -0.0780 2.9258 0.2123 4.0000 4.0000 3.7416 0.0372 -0.0673 0.0799 12.2757 0.0170 0.0029 -0.0589 -0.0575 -0.0806 2.9409 0.1922 4.0000 4.0000 3.7461 0.0193 -0.0718 0.0797 12.2144 0.0153 0.0024 -0.0642 -0.0665 -0.0837 2.9561 0.1659 4.0000 4.0000 3.7547 -0.0047 -0.0775 0.0794 12.1536 0.0132 0.0018 -0.0709 -0.0788 -0.0877 2.9712 0.1249 4.0000 4.0000 3.7775 -0.0431 -0.0862 0.0792 12.0935 0.0099 0.0010 -0.0812 -0.0991 -0.0939 2.9864 0.0652 4.0000 4.0000 3.8652 -0.0996 -0.0986 0.0789 12.0339 0.0051 0.0003 -0.0961 -0.1292 -0.1027 3.0000 0.0116 4.0000 4.0020 4.0020 -0.1505 -0.1097 0.0787 11.9867 0.0009 0.0000 -0.1097 0.0000 0.0000 RADIUS: 3.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.73 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.010073 TOTAL WEIGHT (Kg) = 0.004568 TOTAL VOLUME (IN**3) = 0.164102 TOTAL PROJECTED AREA (IN**2) = 2.5918 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000037 MOMENT OF INERTIA (Kg-M**2) = 0.000004 STATIC MOMENT, ONE SIDE (IN-LB) = 0.004664 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 = 97.062 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 23660.22 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.80, E63 (Transition Start, Airfoil 1) AIRFOIL2: 1.30, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412