15x4E (15x4E.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 1.0000 4.0000 0.0000 0.0000 0.5000 0.0000 0.4000 0.0000 0.4000 0.0000 0.2500 0.0000 0.0000 0.1200 0.9618 4.0000 0.0106 -0.2250 0.4926 0.0087 0.3980 0.8069 0.3828 0.3244 0.2523 0.0139 0.0458 0.2400 0.9221 4.0000 0.0820 -0.4318 0.4831 0.0321 0.3919 3.1138 0.3613 0.3149 0.2585 0.0250 0.0482 0.3600 0.8859 4.0000 0.2664 -0.5313 0.4727 0.0661 0.3817 6.7158 0.3382 0.2952 0.2672 0.0365 0.0537 0.4800 0.8586 4.0000 0.6018 -0.4334 0.4623 0.1067 0.3675 11.2839 0.3156 0.2675 0.2775 0.0478 0.0621 0.6000 0.8438 4.0000 1.1040 -0.0831 0.4531 0.1503 0.3493 16.3221 0.2947 0.2362 0.2884 0.0585 0.0729 0.7200 0.8430 4.0000 1.7549 0.5272 0.4459 0.1931 0.3271 21.2020 0.2757 0.2053 0.2991 0.0683 0.0855 0.8400 0.8551 4.0000 2.4922 1.3353 0.4417 0.2314 0.3048 25.2766 0.2607 0.1774 0.3087 0.0771 0.0994 0.9600 0.8770 4.0000 3.2072 2.1503 0.4415 0.2614 0.2843 27.9998 0.2493 0.1548 0.3163 0.0845 0.1134 1.0800 0.9053 4.0000 3.7576 2.8151 0.4463 0.2793 0.2654 28.9752 0.2403 0.1392 0.3205 0.0896 0.1255 1.2000 0.9382 4.0000 3.9978 3.1425 0.4571 0.2815 0.2481 27.9338 0.2328 0.1331 0.3199 0.0901 0.1322 1.3242 0.9747 4.0000 4.0000 3.1985 0.4717 0.2726 0.2318 25.6766 0.2259 0.1339 0.3157 0.0860 0.1337 1.5202 1.0296 4.0000 4.0000 3.2789 0.4916 0.2593 0.2090 22.7230 0.2152 0.1345 0.3084 0.0787 0.1348 1.7203 1.0827 4.0000 4.0000 3.3553 0.5081 0.2463 0.1894 20.3072 0.2050 0.1351 0.3000 0.0695 0.1342 1.9205 1.1326 4.0000 4.0000 3.4247 0.5209 0.2337 0.1730 18.3395 0.1959 0.1360 0.2909 0.0576 0.1318 2.1207 1.1738 4.0000 4.0000 3.4847 0.5300 0.2211 0.1595 16.7095 0.1872 0.1367 0.2809 0.0449 0.1280 2.3209 1.2053 4.0000 4.0000 3.5339 0.5358 0.2085 0.1486 15.3391 0.1792 0.1366 0.2705 0.0330 0.1234 2.5210 1.2278 4.0000 4.0000 3.5733 0.5383 0.1962 0.1400 14.1722 0.1719 0.1360 0.2600 0.0216 0.1184 2.7212 1.2416 4.0000 4.0000 3.6021 0.5377 0.1842 0.1333 13.1674 0.1655 0.1350 0.2496 0.0106 0.1130 2.9214 1.2475 4.0000 4.0000 3.6208 0.5342 0.1724 0.1281 12.2936 0.1598 0.1336 0.2391 0.0002 0.1073 3.1216 1.2458 4.0000 4.0000 3.6307 0.5280 0.1610 0.1241 11.5270 0.1546 0.1316 0.2286 -0.0095 0.1013 3.3217 1.2372 4.0000 4.0000 3.6338 0.5192 0.1498 0.1210 10.8494 0.1497 0.1290 0.2182 -0.0186 0.0953 3.5219 1.2221 4.0000 4.0000 3.6330 0.5080 0.1392 0.1184 10.2462 0.1447 0.1255 0.2077 -0.0270 0.0893 3.7221 1.2012 4.0000 4.0000 3.6296 0.4946 0.1291 0.1160 9.7059 0.1394 0.1208 0.1973 -0.0347 0.0836 3.9222 1.1748 4.0000 4.0000 3.6167 0.4790 0.1194 0.1138 9.2193 0.1336 0.1152 0.1868 -0.0417 0.0780 4.1224 1.1437 4.0000 4.0000 3.5952 0.4616 0.1102 0.1117 8.7788 0.1277 0.1088 0.1764 -0.0480 0.0726 4.3226 1.1082 4.0000 4.0000 3.5731 0.4425 0.1013 0.1097 8.3782 0.1216 0.1017 0.1659 -0.0536 0.0674 4.5228 1.0690 4.0000 4.0000 3.5519 0.4217 0.0927 0.1079 8.0123 0.1154 0.0942 0.1555 -0.0586 0.0622 4.7229 1.0265 4.0000 4.0000 3.5319 0.3996 0.0843 0.1063 7.6768 0.1091 0.0864 0.1450 -0.0631 0.0572 4.9231 0.9813 4.0000 4.0000 3.5148 0.3762 0.0761 0.1048 7.3682 0.1029 0.0784 0.1346 -0.0671 0.0522 5.1233 0.9340 4.0000 4.0000 3.5005 0.3518 0.0681 0.1035 7.0833 0.0967 0.0705 0.1241 -0.0708 0.0473 5.3234 0.8850 4.0000 4.0000 3.4882 0.3264 0.0601 0.1024 6.8195 0.0906 0.0628 0.1136 -0.0743 0.0422 5.5236 0.8349 4.0000 4.0000 3.4761 0.3004 0.0523 0.1014 6.5746 0.0846 0.0555 0.1032 -0.0781 0.0369 5.7238 0.7842 4.0000 4.0000 3.4633 0.2737 0.0446 0.1005 6.3465 0.0788 0.0487 0.0927 -0.0821 0.0315 5.9240 0.7335 4.0000 4.0000 3.4502 0.2467 0.0369 0.0998 6.1338 0.0732 0.0424 0.0823 -0.0864 0.0258 6.1241 0.6833 4.0000 4.0000 3.4367 0.2194 0.0292 0.0993 5.9347 0.0679 0.0367 0.0718 -0.0911 0.0199 6.3243 0.6341 4.0000 4.0000 3.4225 0.1921 0.0215 0.0989 5.7482 0.0627 0.0315 0.0614 -0.0963 0.0137 6.5245 0.5864 4.0000 4.0000 3.4067 0.1649 0.0137 0.0987 5.5729 0.0579 0.0270 0.0509 -0.1019 0.0073 6.7247 0.5409 4.0000 4.0000 3.3890 0.1379 0.0058 0.0987 5.4080 0.0534 0.0229 0.0405 -0.1083 0.0006 6.9248 0.4979 4.0000 4.0000 3.3689 0.1114 -0.0022 0.0988 5.2526 0.0492 0.0194 0.0300 -0.1152 -0.0064 7.1165 0.4598 4.0000 4.0000 3.3078 0.0865 -0.0100 0.0991 5.1119 0.0455 0.0166 0.0193 -0.1226 -0.0140 7.1629 0.4510 4.0000 4.0000 3.2623 0.0806 -0.0120 0.0991 5.0790 0.0447 0.0160 0.0162 -0.1245 -0.0164 7.2008 0.4437 4.0000 4.0000 3.2135 0.0755 -0.0136 0.0992 5.0524 0.0440 0.0155 0.0134 -0.1263 -0.0185 7.2386 0.4325 4.0000 4.0000 3.1528 0.0664 -0.0155 0.0993 5.0261 0.0429 0.0147 0.0100 -0.1303 -0.0210 7.2765 0.4162 4.0000 4.0000 3.0851 0.0521 -0.0180 0.0994 5.0001 0.0414 0.0136 0.0057 -0.1371 -0.0240 7.3144 0.3940 4.0000 4.0000 2.8470 0.0318 -0.0209 0.0995 4.9743 0.0392 0.0122 0.0005 -0.1474 -0.0275 7.3523 0.3643 4.0000 4.0000 2.5638 0.0039 -0.0245 0.0996 4.9488 0.0363 0.0105 -0.0057 -0.1619 -0.0316 7.3902 0.3240 4.0000 4.0000 2.2727 -0.0346 -0.0291 0.0997 4.9236 0.0323 0.0083 -0.0133 -0.1824 -0.0363 7.4280 0.2646 4.0000 4.0000 2.0228 -0.0923 -0.0352 0.0998 4.8986 0.0264 0.0056 -0.0231 -0.2133 -0.0419 7.4659 0.1485 4.0000 4.0000 2.2585 -0.2066 -0.0462 0.0999 4.8738 0.0148 0.0018 -0.0399 -0.2756 -0.0505 7.5000 0.0197 4.0000 4.0020 4.0020 -0.3339 -0.0579 0.1000 4.8542 0.0020 0.0000 -0.0579 0.0000 0.0000 RADIUS: 7.50 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.102376 TOTAL WEIGHT (Kg) = 0.046429 TOTAL VOLUME (IN**3) = 1.667831 TOTAL PROJECTED AREA (IN**2) = 13.6728 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002494 MOMENT OF INERTIA (Kg-M**2) = 0.000282 STATIC MOMENT, ONE SIDE (IN-LB) = 0.125542 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 = 73.545 INNER LIMIT (NORMALIZED BY RADIUS) = 0.067 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 8381.11 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.20, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.12, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412