7x15E (7x15E.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 0.6500 -2.7224 0.0000 0.0000 0.3250 0.0000 0.3846 0.0000 0.2500 0.0000 0.0900 0.0000 0.0000 0.0750 0.6204 -0.9057 0.0123 -0.2297 0.3177 0.0081 0.3829 1.4938 0.2375 0.1370 0.0956 0.0081 -0.0336 0.1500 0.5815 0.8109 0.0981 -0.4552 0.3045 0.0299 0.3776 5.9453 0.2196 0.1401 0.1109 0.0168 -0.0317 0.2250 0.5430 2.4276 0.3358 -0.6513 0.2872 0.0622 0.3688 13.3608 0.2003 0.1435 0.1331 0.0260 -0.0284 0.3000 0.5165 3.9443 0.8159 -0.6496 0.2678 0.1012 0.3566 23.4062 0.1842 0.1381 0.1567 0.0337 -0.0200 0.3750 0.5113 5.3610 1.6454 -0.2582 0.2482 0.1435 0.3408 34.9276 0.1742 0.1254 0.1814 0.0404 -0.0079 0.4500 0.5298 6.6777 2.9352 0.7134 0.2300 0.1858 0.3215 46.0717 0.1704 0.1093 0.2083 0.0466 0.0057 0.5250 0.5662 7.8944 4.7533 2.4102 0.2149 0.2251 0.2988 55.2404 0.1692 0.0929 0.2370 0.0527 0.0183 0.6000 0.6097 9.0110 7.0134 4.6336 0.2047 0.2579 0.2725 61.7408 0.1661 0.0787 0.2641 0.0586 0.0281 0.6750 0.6488 10.0277 9.3192 7.0889 0.2010 0.2810 0.2440 65.5298 0.1583 0.0682 0.2851 0.0642 0.0335 0.7500 0.6742 10.9444 10.9375 8.9492 0.2056 0.2912 0.2190 66.6913 0.1477 0.0624 0.2949 0.0698 0.0335 0.8256 0.6878 11.7670 11.7670 9.9820 0.2155 0.2919 0.1976 66.2105 0.1359 0.0595 0.2957 0.0749 0.0302 0.9112 0.7009 12.5763 12.5763 11.0677 0.2255 0.2916 0.1776 65.5228 0.1245 0.0565 0.2954 0.0790 0.0263 0.9974 0.7117 13.2593 13.2593 11.9677 0.2342 0.2902 0.1615 64.7025 0.1149 0.0538 0.2941 0.0813 0.0224 1.0836 0.7201 13.8102 13.8102 12.7295 0.2416 0.2877 0.1490 63.7562 0.1073 0.0516 0.2918 0.0821 0.0186 1.1698 0.7262 14.2291 14.2291 13.3066 0.2478 0.2843 0.1395 62.6807 0.1013 0.0499 0.2884 0.0815 0.0153 1.2560 0.7302 14.5158 14.5158 13.7134 0.2527 0.2799 0.1327 61.4681 0.0969 0.0485 0.2842 0.0795 0.0124 1.3422 0.7319 14.6703 14.6703 13.9518 0.2564 0.2747 0.1279 60.1067 0.0936 0.0475 0.2791 0.0762 0.0102 1.4284 0.7316 14.7000 14.7000 14.0423 0.2591 0.2686 0.1247 58.5935 0.0912 0.0466 0.2732 0.0716 0.0087 1.5147 0.7293 14.7000 14.7000 14.0831 0.2606 0.2617 0.1226 57.0808 0.0894 0.0458 0.2666 0.0667 0.0073 1.6009 0.7249 14.7000 14.7000 14.1151 0.2610 0.2540 0.1211 55.6180 0.0878 0.0450 0.2591 0.0615 0.0058 1.6871 0.7187 14.7000 14.7000 14.1463 0.2604 0.2456 0.1198 54.2046 0.0861 0.0440 0.2510 0.0563 0.0041 1.7733 0.7106 14.7000 14.7000 14.1781 0.2588 0.2366 0.1184 52.8398 0.0842 0.0428 0.2423 0.0509 0.0022 1.8595 0.7008 14.7000 14.7000 14.2080 0.2562 0.2270 0.1171 51.5225 0.0821 0.0415 0.2330 0.0455 0.0002 1.9457 0.6892 14.7000 14.7000 14.2363 0.2527 0.2169 0.1159 50.2517 0.0799 0.0400 0.2232 0.0401 -0.0020 2.0319 0.6760 14.7000 14.7000 14.2622 0.2483 0.2063 0.1147 49.0261 0.0776 0.0384 0.2129 0.0348 -0.0042 2.1181 0.6612 14.7000 14.7000 14.2860 0.2431 0.1954 0.1136 47.8443 0.0751 0.0366 0.2022 0.0295 -0.0067 2.2043 0.6449 14.7000 14.7000 14.3066 0.2370 0.1841 0.1126 46.7051 0.0726 0.0348 0.1911 0.0244 -0.0092 2.2905 0.6272 14.7000 14.7000 14.3241 0.2302 0.1725 0.1116 45.6071 0.0700 0.0329 0.1796 0.0193 -0.0120 2.3767 0.6080 14.7000 14.7000 14.3376 0.2226 0.1606 0.1107 44.5487 0.0673 0.0309 0.1679 0.0144 -0.0149 2.4629 0.5876 14.7000 14.7000 14.3491 0.2144 0.1485 0.1099 43.5287 0.0646 0.0288 0.1560 0.0096 -0.0179 2.5491 0.5658 14.7000 14.7000 14.3597 0.2054 0.1363 0.1091 42.5455 0.0617 0.0267 0.1439 0.0050 -0.0210 2.6353 0.5429 14.7000 14.7000 14.3700 0.1959 0.1239 0.1084 41.5977 0.0588 0.0246 0.1316 0.0006 -0.0241 2.7216 0.5188 14.7000 14.7000 14.3803 0.1857 0.1116 0.1078 40.6839 0.0559 0.0225 0.1193 -0.0036 -0.0273 2.8078 0.4937 14.7000 14.7000 14.3898 0.1750 0.0993 0.1072 39.8029 0.0529 0.0204 0.1070 -0.0076 -0.0306 2.8940 0.4675 14.7000 14.7000 14.3945 0.1638 0.0870 0.1067 38.9532 0.0499 0.0183 0.0946 -0.0115 -0.0342 2.9802 0.4404 14.7000 14.7000 14.3932 0.1521 0.0749 0.1062 38.1336 0.0468 0.0163 0.0822 -0.0151 -0.0379 3.0664 0.4124 14.6859 14.6859 14.3707 0.1400 0.0631 0.1059 37.3163 0.0437 0.0143 0.0698 -0.0186 -0.0417 3.1526 0.3836 14.6255 14.6255 14.2943 0.1274 0.0514 0.1056 36.4404 0.0405 0.0124 0.0576 -0.0220 -0.0452 3.2388 0.3541 14.5175 14.5175 14.0504 0.1145 0.0400 0.1053 35.5038 0.0373 0.0106 0.0456 -0.0254 -0.0485 3.3214 0.3251 14.3694 14.3694 13.6602 0.1018 0.0294 0.1052 34.5493 0.0342 0.0090 0.0344 -0.0279 -0.0510 3.3427 0.3164 14.3242 14.3242 13.5264 0.0975 0.0261 0.1051 34.2948 0.0333 0.0085 0.0308 -0.0289 -0.0518 3.3604 0.3065 14.2845 14.2845 13.4037 0.0918 0.0219 0.1051 34.0803 0.0322 0.0079 0.0265 -0.0307 -0.0532 3.3780 0.2942 14.2427 14.2427 13.2700 0.0840 0.0164 0.1051 33.8632 0.0309 0.0073 0.0207 -0.0335 -0.0553 3.3957 0.2789 14.1989 14.1989 13.1248 0.0738 0.0093 0.1051 33.6436 0.0293 0.0065 0.0134 -0.0374 -0.0582 3.4134 0.2602 14.1532 14.1532 12.9743 0.0607 0.0004 0.1050 33.4214 0.0273 0.0056 0.0042 -0.0429 -0.0622 3.4311 0.2369 14.1054 14.1054 12.8417 0.0436 -0.0109 0.1050 33.1967 0.0249 0.0046 -0.0075 -0.0505 -0.0675 3.4487 0.2066 14.0556 14.0556 12.7079 0.0207 -0.0258 0.1050 32.9695 0.0217 0.0035 -0.0229 -0.0613 -0.0748 3.4664 0.1624 14.0039 14.0039 12.5906 -0.0141 -0.0481 0.1050 32.7396 0.0171 0.0021 -0.0458 -0.0783 -0.0863 3.4841 0.0857 13.9501 13.9501 12.6252 -0.0764 -0.0875 0.1050 32.5072 0.0090 0.0006 -0.0864 -0.1104 -0.1077 3.5000 0.0130 13.9000 13.9127 13.9126 -0.1358 -0.1246 0.1050 32.3195 0.0014 0.0000 -0.1246 0.0000 0.0000 RADIUS: 3.50 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.021798 TOTAL WEIGHT (Kg) = 0.009886 TOTAL VOLUME (IN**3) = 0.355115 TOTAL PROJECTED AREA (IN**2) = 2.6502 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000109 MOMENT OF INERTIA (Kg-M**2) = 0.000012 STATIC MOMENT, ONE SIDE (IN-LB) = 0.011729 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 = 105.000 INNER LIMIT (NORMALIZED BY RADIUS) = 0.093 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 24059.80 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.80, E66 (Transition Start, Airfoil 1) AIRFOIL2: 3.35, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412