15x7E (15x7E.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 6.3951 0.0000 0.0000 0.5000 0.0000 0.3450 0.0000 0.3450 0.0000 0.2050 0.0000 0.0000 0.1200 0.9575 6.4769 0.0144 -0.2118 0.4926 0.0142 0.3440 1.0922 0.3294 0.2839 0.2135 0.0156 0.0334 0.2400 0.9069 6.5528 0.1128 -0.4103 0.4831 0.0527 0.3411 4.2797 0.3093 0.2834 0.2365 0.0327 0.0450 0.3600 0.8577 6.6227 0.3752 -0.4803 0.4727 0.1089 0.3362 9.4186 0.2883 0.2713 0.2687 0.0525 0.0652 0.4800 0.8199 6.6867 0.8747 -0.2873 0.4623 0.1768 0.3293 16.1737 0.2700 0.2489 0.3071 0.0733 0.0924 0.6000 0.8013 6.7448 1.6655 0.2766 0.4531 0.2505 0.3204 23.8354 0.2568 0.2217 0.3489 0.0935 0.1242 0.7200 0.8050 6.7969 2.7556 1.2671 0.4459 0.3242 0.3096 31.3468 0.2492 0.1943 0.3917 0.1118 0.1584 0.8400 0.8278 6.8431 4.0672 2.5927 0.4417 0.3919 0.2968 37.6185 0.2457 0.1700 0.4330 0.1268 0.1924 0.9600 0.8626 6.8833 5.4039 4.0113 0.4415 0.4478 0.2821 41.8571 0.2433 0.1509 0.4697 0.1373 0.2235 1.0800 0.9011 6.9176 6.4658 5.2062 0.4463 0.4861 0.2654 43.6164 0.2391 0.1384 0.4974 0.1421 0.2483 1.2000 0.9382 6.9459 6.9419 5.8111 0.4571 0.5007 0.2481 42.6358 0.2328 0.1339 0.5094 0.1398 0.2625 1.3242 0.9747 6.9690 6.9690 5.9378 0.4717 0.4978 0.2318 39.9498 0.2259 0.1347 0.5086 0.1321 0.2676 1.5202 1.0296 6.9924 6.9924 6.1040 0.4916 0.4887 0.2090 36.2068 0.2152 0.1351 0.5032 0.1191 0.2711 1.7203 1.0827 7.0000 7.0000 6.2382 0.5081 0.4740 0.1894 32.9268 0.2050 0.1354 0.4924 0.1046 0.2688 1.9205 1.1326 7.0000 7.0000 6.3442 0.5209 0.4542 0.1730 30.1179 0.1959 0.1362 0.4764 0.0882 0.2601 2.1207 1.1738 7.0000 7.0000 6.4288 0.5300 0.4293 0.1595 27.7148 0.1872 0.1368 0.4550 0.0717 0.2457 2.3209 1.2053 7.0000 7.0000 6.4942 0.5358 0.4019 0.1486 25.6424 0.1792 0.1367 0.4309 0.0565 0.2287 2.5210 1.2278 7.0000 7.0000 6.5458 0.5383 0.3758 0.1400 23.8414 0.1719 0.1361 0.4080 0.0422 0.2128 2.7212 1.2416 7.0000 7.0000 6.5843 0.5377 0.3510 0.1333 22.2646 0.1655 0.1351 0.3862 0.0287 0.1979 2.9214 1.2475 7.0000 7.0000 6.6109 0.5342 0.3275 0.1281 20.8746 0.1598 0.1336 0.3656 0.0161 0.1840 3.1216 1.2458 7.0000 7.0000 6.6277 0.5280 0.3053 0.1241 19.6415 0.1546 0.1317 0.3460 0.0044 0.1711 3.3217 1.2372 7.0000 7.0000 6.6363 0.5192 0.2845 0.1210 18.5411 0.1497 0.1290 0.3273 -0.0064 0.1591 3.5219 1.2221 7.0000 7.0000 6.6393 0.5080 0.2650 0.1184 17.5538 0.1447 0.1255 0.3096 -0.0162 0.1482 3.7221 1.2012 7.0000 7.0000 6.6393 0.4946 0.2468 0.1160 16.6634 0.1394 0.1208 0.2927 -0.0252 0.1383 3.9222 1.1748 7.0000 7.0000 6.6291 0.4790 0.2300 0.1138 15.8568 0.1336 0.1152 0.2766 -0.0334 0.1294 4.1224 1.1437 7.0000 7.0000 6.6097 0.4616 0.2144 0.1117 15.1230 0.1277 0.1088 0.2612 -0.0407 0.1215 4.3226 1.1082 7.0000 7.0000 6.5893 0.4425 0.1999 0.1097 14.4526 0.1216 0.1018 0.2466 -0.0473 0.1144 4.5228 1.0690 7.0000 7.0000 6.5693 0.4217 0.1864 0.1079 13.8381 0.1154 0.0942 0.2326 -0.0531 0.1080 4.7229 1.0265 7.0000 7.0000 6.5511 0.3996 0.1738 0.1063 13.2728 0.1091 0.0864 0.2191 -0.0583 0.1024 4.9231 0.9813 7.0000 7.0000 6.5347 0.3762 0.1621 0.1048 12.7511 0.1029 0.0784 0.2062 -0.0629 0.0973 5.1233 0.9340 7.0000 7.0000 6.5215 0.3518 0.1511 0.1035 12.2683 0.0967 0.0705 0.1938 -0.0672 0.0927 5.3234 0.8850 7.0000 7.0000 6.5103 0.3264 0.1407 0.1024 11.8202 0.0906 0.0628 0.1817 -0.0713 0.0883 5.5236 0.8349 7.0000 7.0000 6.4983 0.3004 0.1307 0.1014 11.4033 0.0846 0.0555 0.1700 -0.0755 0.0840 5.7238 0.7842 7.0000 7.0000 6.4863 0.2737 0.1212 0.1005 11.0144 0.0788 0.0487 0.1587 -0.0799 0.0796 5.9240 0.7335 7.0000 7.0000 6.4739 0.2467 0.1120 0.0998 10.6509 0.0732 0.0424 0.1475 -0.0845 0.0750 6.1241 0.6833 7.0000 7.0000 6.4610 0.2194 0.1030 0.0993 10.3103 0.0679 0.0367 0.1366 -0.0895 0.0703 6.3243 0.6341 7.0000 7.0000 6.4468 0.1921 0.0941 0.0989 9.9907 0.0627 0.0315 0.1258 -0.0949 0.0654 6.5245 0.5864 7.0000 7.0000 6.4314 0.1649 0.0853 0.0987 9.6901 0.0579 0.0270 0.1150 -0.1008 0.0601 6.7247 0.5409 7.0000 7.0000 6.4143 0.1379 0.0765 0.0987 9.4068 0.0534 0.0229 0.1043 -0.1073 0.0544 6.9248 0.4979 7.0000 7.0000 6.3947 0.1114 0.0676 0.0988 9.1396 0.0492 0.0194 0.0935 -0.1144 0.0483 7.1165 0.4598 7.0000 7.0000 6.3331 0.0865 0.0589 0.0991 8.8974 0.0455 0.0166 0.0825 -0.1220 0.0412 7.1629 0.4510 7.0000 7.0000 6.2878 0.0806 0.0567 0.0991 8.8407 0.0447 0.0160 0.0794 -0.1239 0.0390 7.2008 0.4438 7.0000 7.0000 6.2390 0.0756 0.0549 0.0992 8.7949 0.0440 0.0155 0.0766 -0.1256 0.0370 7.2386 0.4329 7.0000 7.0000 6.1777 0.0668 0.0525 0.0993 8.7496 0.0430 0.0147 0.0730 -0.1294 0.0344 7.2765 0.4168 7.0000 7.0000 6.1053 0.0528 0.0493 0.0994 8.7048 0.0414 0.0137 0.0683 -0.1362 0.0311 7.3144 0.3947 7.0000 7.0000 5.8444 0.0327 0.0451 0.0995 8.6604 0.0393 0.0123 0.0624 -0.1463 0.0271 7.3523 0.3651 7.0000 7.0000 5.5537 0.0051 0.0399 0.0996 8.6164 0.0363 0.0105 0.0550 -0.1606 0.0223 7.3902 0.3248 7.0000 7.0000 5.2543 -0.0331 0.0330 0.0997 8.5729 0.0324 0.0083 0.0457 -0.1808 0.0164 7.4280 0.2656 7.0000 7.0000 4.9959 -0.0903 0.0233 0.0998 8.5299 0.0265 0.0056 0.0330 -0.2114 0.0089 7.4659 0.1494 7.0000 7.0000 5.2253 -0.2039 0.0053 0.0999 8.4872 0.0149 0.0018 0.0104 -0.2731 -0.0035 7.5000 0.0197 7.0000 7.0035 7.0035 -0.3311 -0.0144 0.1000 8.4534 0.0020 0.0000 -0.0144 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) = 0.099907 TOTAL WEIGHT (Kg) = 0.045309 TOTAL VOLUME (IN**3) = 1.627605 TOTAL PROJECTED AREA (IN**2) = 13.0170 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002494 MOMENT OF INERTIA (Kg-M**2) = 0.000282 STATIC MOMENT, ONE SIDE (IN-LB) = 0.125187 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) = 8306.71 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