15x6E (15x6E.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 6.0000 0.0000 0.0000 0.5000 0.0000 0.3650 0.0000 0.3650 0.0000 0.2200 0.0000 0.0000 0.1200 0.9587 6.0000 0.0135 -0.2188 0.4926 0.0133 0.3637 1.0294 0.3487 0.2989 0.2272 0.0151 0.0374 0.2400 0.9112 6.0000 0.1058 -0.4226 0.4831 0.0493 0.3600 4.0148 0.3280 0.2957 0.2467 0.0305 0.0477 0.3600 0.8659 6.0000 0.3493 -0.5024 0.4727 0.1018 0.3536 8.7786 0.3062 0.2808 0.2743 0.0479 0.0656 0.4800 0.8313 6.0000 0.8063 -0.3354 0.4623 0.1652 0.3448 14.9673 0.2866 0.2563 0.3071 0.0660 0.0900 0.6000 0.8141 6.0000 1.5169 0.1693 0.4531 0.2338 0.3335 21.9181 0.2715 0.2273 0.3428 0.0835 0.1187 0.7200 0.8166 6.0000 2.4763 1.0488 0.4459 0.3022 0.3196 28.6959 0.2610 0.1984 0.3792 0.0991 0.1498 0.8400 0.8363 6.0000 3.6059 2.2206 0.4417 0.3648 0.3032 34.3415 0.2536 0.1728 0.4140 0.1121 0.1811 0.9600 0.8671 6.0000 4.7341 3.4444 0.4415 0.4160 0.2843 38.1265 0.2465 0.1524 0.4444 0.1213 0.2103 1.0800 0.9025 6.0000 5.6145 4.4600 0.4463 0.4503 0.2654 39.6040 0.2395 0.1389 0.4666 0.1256 0.2339 1.2000 0.9382 6.0000 5.9966 4.9617 0.4571 0.4622 0.2481 38.4961 0.2328 0.1338 0.4757 0.1236 0.2477 1.3242 0.9747 6.0000 6.0000 5.0517 0.4717 0.4575 0.2318 35.7972 0.2259 0.1345 0.4742 0.1164 0.2526 1.5202 1.0296 6.0000 6.0000 5.1744 0.4916 0.4466 0.2090 32.1359 0.2152 0.1350 0.4684 0.1046 0.2561 1.7203 1.0827 6.0000 6.0000 5.2834 0.5081 0.4317 0.1894 29.0338 0.2050 0.1353 0.4583 0.0916 0.2544 1.9205 1.1326 6.0000 6.0000 5.3760 0.5209 0.4131 0.1730 26.4377 0.1959 0.1362 0.4437 0.0766 0.2471 2.1207 1.1738 6.0000 6.0000 5.4516 0.5300 0.3906 0.1595 24.2417 0.1872 0.1368 0.4247 0.0614 0.2349 2.3209 1.2053 6.0000 6.0000 5.5111 0.5358 0.3661 0.1486 22.3649 0.1792 0.1367 0.4036 0.0473 0.2205 2.5210 1.2278 6.0000 6.0000 5.5587 0.5383 0.3430 0.1400 20.7459 0.1719 0.1361 0.3834 0.0339 0.2069 2.7212 1.2416 6.0000 6.0000 5.5943 0.5377 0.3210 0.1333 19.3371 0.1655 0.1350 0.3642 0.0214 0.1940 2.9214 1.2475 6.0000 6.0000 5.6176 0.5342 0.3002 0.1281 18.1013 0.1598 0.1336 0.3459 0.0096 0.1817 3.1216 1.2458 6.0000 6.0000 5.6309 0.5280 0.2805 0.1241 17.0097 0.1546 0.1317 0.3284 -0.0013 0.1702 3.3217 1.2372 6.0000 6.0000 5.6368 0.5192 0.2620 0.1210 16.0389 0.1497 0.1290 0.3118 -0.0114 0.1595 3.5219 1.2221 6.0000 6.0000 5.6384 0.5080 0.2448 0.1184 15.1705 0.1447 0.1255 0.2959 -0.0207 0.1496 3.7221 1.2012 6.0000 6.0000 5.6372 0.4946 0.2287 0.1160 14.3894 0.1394 0.1208 0.2807 -0.0291 0.1407 3.9222 1.1748 6.0000 6.0000 5.6260 0.4790 0.2139 0.1138 13.6833 0.1336 0.1152 0.2662 -0.0368 0.1325 4.1224 1.1437 6.0000 6.0000 5.6059 0.4616 0.2001 0.1117 13.0422 0.1277 0.1088 0.2523 -0.0438 0.1252 4.3226 1.1082 6.0000 6.0000 5.5849 0.4425 0.1872 0.1097 12.4575 0.1216 0.1017 0.2389 -0.0500 0.1186 4.5228 1.0690 6.0000 6.0000 5.5645 0.4217 0.1753 0.1079 11.9223 0.1154 0.0942 0.2261 -0.0555 0.1126 4.7229 1.0265 6.0000 6.0000 5.5456 0.3996 0.1641 0.1063 11.4305 0.1091 0.0864 0.2137 -0.0603 0.1072 4.9231 0.9813 6.0000 6.0000 5.5289 0.3762 0.1535 0.1048 10.9773 0.1029 0.0784 0.2017 -0.0647 0.1022 5.1233 0.9340 6.0000 6.0000 5.5153 0.3518 0.1436 0.1035 10.5582 0.0967 0.0705 0.1901 -0.0687 0.0976 5.3234 0.8850 6.0000 6.0000 5.5037 0.3264 0.1342 0.1024 10.1697 0.0906 0.0628 0.1788 -0.0726 0.0931 5.5236 0.8349 6.0000 6.0000 5.4917 0.3004 0.1251 0.1014 9.8084 0.0846 0.0555 0.1677 -0.0766 0.0887 5.7238 0.7842 6.0000 6.0000 5.4793 0.2737 0.1164 0.1005 9.4717 0.0788 0.0487 0.1569 -0.0809 0.0841 5.9240 0.7335 6.0000 6.0000 5.4667 0.2467 0.1078 0.0998 9.1572 0.0732 0.0424 0.1462 -0.0854 0.0794 6.1241 0.6833 6.0000 6.0000 5.4536 0.2194 0.0995 0.0993 8.8627 0.0679 0.0367 0.1357 -0.0902 0.0745 6.3243 0.6341 6.0000 6.0000 5.4394 0.1921 0.0911 0.0989 8.5864 0.0627 0.0315 0.1252 -0.0955 0.0693 6.5245 0.5864 6.0000 6.0000 5.4238 0.1649 0.0828 0.0987 8.3267 0.0579 0.0270 0.1147 -0.1013 0.0638 6.7247 0.5409 6.0000 6.0000 5.4065 0.1379 0.0744 0.0987 8.0822 0.0534 0.0229 0.1042 -0.1077 0.0579 6.9248 0.4979 6.0000 6.0000 5.3867 0.1114 0.0658 0.0988 7.8515 0.0492 0.0194 0.0936 -0.1148 0.0515 7.1165 0.4598 6.0000 6.0000 5.3253 0.0865 0.0573 0.0991 7.6426 0.0455 0.0166 0.0826 -0.1223 0.0442 7.1629 0.4510 6.0000 6.0000 5.2799 0.0806 0.0552 0.0991 7.5937 0.0447 0.0160 0.0795 -0.1242 0.0419 7.2008 0.4438 6.0000 6.0000 5.2311 0.0755 0.0534 0.0992 7.5542 0.0440 0.0155 0.0767 -0.1259 0.0398 7.2386 0.4327 6.0000 6.0000 5.1703 0.0666 0.0511 0.0993 7.5151 0.0430 0.0147 0.0731 -0.1298 0.0372 7.2765 0.4166 6.0000 6.0000 5.0994 0.0525 0.0481 0.0994 7.4765 0.0414 0.0137 0.0685 -0.1366 0.0340 7.3144 0.3944 6.0000 6.0000 4.8465 0.0324 0.0443 0.0995 7.4382 0.0392 0.0123 0.0628 -0.1468 0.0301 7.3523 0.3648 6.0000 6.0000 4.5585 0.0046 0.0396 0.0996 7.4003 0.0363 0.0105 0.0558 -0.1612 0.0255 7.3902 0.3245 6.0000 6.0000 4.2622 -0.0337 0.0335 0.0997 7.3628 0.0323 0.0083 0.0470 -0.1814 0.0200 7.4280 0.2652 6.0000 6.0000 4.0069 -0.0911 0.0249 0.0998 7.3256 0.0265 0.0056 0.0353 -0.2122 0.0130 7.4659 0.1490 6.0000 6.0000 4.2385 -0.2050 0.0092 0.0999 7.2889 0.0149 0.0018 0.0146 -0.2741 0.0019 7.5000 0.0197 6.0000 6.0030 6.0030 -0.3322 -0.0079 0.1000 7.2597 0.0020 0.0000 -0.0079 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) = 0.100861 TOTAL WEIGHT (Kg) = 0.045742 TOTAL VOLUME (IN**3) = 1.643162 TOTAL PROJECTED AREA (IN**2) = 13.2449 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002494 MOMENT OF INERTIA (Kg-M**2) = 0.000282 STATIC MOMENT, ONE SIDE (IN-LB) = 0.125330 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) = 8344.38 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