26x15E (26x15E.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 1.7500 15.0000 0.0000 0.0000 0.8750 0.0000 0.2743 0.0000 0.4800 0.0000 0.2500 0.0000 0.0000 0.3380 1.6544 15.0000 0.0442 -0.5562 0.8606 0.0287 0.2728 1.1910 0.4513 0.6871 0.2713 0.0348 0.0210 0.6760 1.5757 15.0000 0.3432 -0.8935 0.8511 0.1053 0.2682 4.6200 0.4226 0.6560 0.3257 0.0703 0.0571 1.0140 1.5244 15.0000 1.1129 -0.6694 0.8460 0.2170 0.2606 9.9082 0.3973 0.6118 0.4047 0.1051 0.1122 1.3520 1.5108 15.0000 2.4930 0.3668 0.8451 0.3513 0.2500 16.3552 0.3777 0.5615 0.5011 0.1377 0.1810 1.6900 1.5388 15.0000 4.5058 2.3149 0.8479 0.4954 0.2364 22.9933 0.3638 0.5102 0.6070 0.1664 0.2581 2.0280 1.6039 15.0000 7.0232 5.0640 0.8541 0.6367 0.2197 28.8624 0.3524 0.4618 0.7140 0.1902 0.3379 2.3660 1.6939 15.0000 9.7590 8.0615 0.8633 0.7627 0.2000 33.2834 0.3388 0.4189 0.8126 0.2078 0.4138 2.7040 1.7939 15.0000 12.3026 10.8692 0.8751 0.8607 0.1802 35.9089 0.3232 0.3836 0.8922 0.2177 0.4784 3.0420 1.8900 15.0000 14.1900 13.0194 0.8892 0.9181 0.1632 36.5905 0.3085 0.3584 0.9399 0.2173 0.5218 3.3800 1.9730 15.0000 14.9929 14.0462 0.9052 0.9223 0.1489 35.2210 0.2938 0.3465 0.9421 0.2017 0.5320 3.7159 2.0399 15.0000 15.0000 14.2109 0.9197 0.8893 0.1371 32.7192 0.2797 0.3444 0.9125 0.1739 0.5163 4.0157 2.0864 15.0000 15.0000 14.3255 0.9280 0.8590 0.1284 30.7317 0.2679 0.3428 0.8859 0.1488 0.5010 4.3133 2.1209 15.0000 15.0000 14.4170 0.9321 0.8283 0.1213 28.9636 0.2573 0.3417 0.8595 0.1236 0.4847 4.6110 2.1443 15.0000 15.0000 14.4859 0.9323 0.7973 0.1156 27.3728 0.2479 0.3413 0.8331 0.0983 0.4672 4.9086 2.1573 15.0000 15.0000 14.5319 0.9287 0.7660 0.1111 25.9361 0.2398 0.3415 0.8066 0.0734 0.4489 5.2063 2.1605 15.0000 15.0000 14.5536 0.9215 0.7345 0.1078 24.6337 0.2329 0.3419 0.7801 0.0493 0.4303 5.5039 2.1543 15.0000 15.0000 14.5481 0.9109 0.7032 0.1053 23.4487 0.2270 0.3420 0.7537 0.0265 0.4118 5.8016 2.1394 15.0000 15.0000 14.5125 0.8970 0.6721 0.1037 22.3669 0.2219 0.3412 0.7273 0.0054 0.3939 6.0992 2.1164 15.0000 15.0000 14.4663 0.8801 0.6417 0.1027 21.3760 0.2173 0.3387 0.7010 -0.0137 0.3768 6.3969 2.0858 15.0000 15.0000 14.4161 0.8604 0.6119 0.1021 20.4656 0.2131 0.3340 0.6747 -0.0306 0.3608 6.6946 2.0483 15.0000 15.0000 14.3670 0.8380 0.5829 0.1019 19.6266 0.2088 0.3264 0.6484 -0.0451 0.3461 6.9922 2.0043 15.0000 15.0000 14.3213 0.8131 0.5548 0.1018 18.8513 0.2040 0.3154 0.6220 -0.0573 0.3327 7.2899 1.9546 15.0000 15.0000 14.2806 0.7858 0.5277 0.1017 18.1329 0.1987 0.3013 0.5956 -0.0673 0.3204 7.5875 1.8996 15.0000 15.0000 14.2497 0.7565 0.5013 0.1015 17.4656 0.1928 0.2846 0.5692 -0.0755 0.3091 7.8852 1.8400 15.0000 15.0000 14.2220 0.7252 0.4753 0.1014 16.8443 0.1865 0.2668 0.5428 -0.0829 0.2977 8.1828 1.7764 15.0000 15.0000 14.1951 0.6921 0.4497 0.1012 16.2645 0.1798 0.2485 0.5164 -0.0899 0.2859 8.4805 1.7092 15.0000 15.0000 14.1692 0.6574 0.4243 0.1011 15.7223 0.1728 0.2300 0.4900 -0.0968 0.2736 8.7781 1.6392 15.0000 15.0000 14.1444 0.6214 0.3992 0.1010 15.2143 0.1655 0.2114 0.4636 -0.1036 0.2609 9.0758 1.5668 15.0000 15.0000 14.1207 0.5841 0.3744 0.1008 14.7374 0.1580 0.1931 0.4373 -0.1103 0.2478 9.3734 1.4927 15.0000 15.0000 14.0984 0.5458 0.3498 0.1007 14.2889 0.1503 0.1753 0.4109 -0.1172 0.2341 9.6711 1.4175 15.0000 15.0000 14.0776 0.5066 0.3254 0.1006 13.8663 0.1425 0.1580 0.3845 -0.1242 0.2200 9.9688 1.3417 15.0000 15.0000 14.0584 0.4668 0.3011 0.1004 13.4676 0.1347 0.1416 0.3581 -0.1315 0.2053 10.2664 1.2659 15.0000 15.0000 14.0409 0.4265 0.2771 0.1003 13.0908 0.1270 0.1261 0.3317 -0.1391 0.1902 10.5641 1.1907 15.0000 15.0000 14.0253 0.3859 0.2531 0.1002 12.7341 0.1192 0.1116 0.3053 -0.1472 0.1745 10.8617 1.1166 15.0000 15.0000 14.0115 0.3451 0.2292 0.1000 12.3961 0.1117 0.0982 0.2789 -0.1558 0.1582 11.1594 1.0443 15.0000 15.0000 13.9992 0.3044 0.2053 0.0999 12.0753 0.1043 0.0859 0.2525 -0.1650 0.1414 11.4570 0.9744 15.0000 15.0000 13.9884 0.2640 0.1814 0.0998 11.7704 0.0972 0.0749 0.2261 -0.1748 0.1239 11.7547 0.9074 15.0000 15.0000 13.9789 0.2240 0.1575 0.0997 11.4804 0.0905 0.0650 0.1997 -0.1854 0.1059 12.0523 0.8439 15.0000 15.0000 13.9704 0.1846 0.1335 0.0997 11.2041 0.0842 0.0563 0.1733 -0.1969 0.0872 12.3379 0.7868 15.0000 15.0000 13.9625 0.1475 0.1104 0.0997 10.9511 0.0785 0.0490 0.1480 -0.2088 0.0687 12.4157 0.7719 15.0000 15.0000 13.9604 0.1376 0.1041 0.0998 10.8842 0.0770 0.0472 0.1411 -0.2122 0.0635 12.4813 0.7596 15.0000 15.0000 13.9585 0.1292 0.0988 0.0998 10.8283 0.0758 0.0457 0.1353 -0.2151 0.0592 12.5470 0.7419 15.0000 15.0000 13.9453 0.1153 0.0924 0.0998 10.7730 0.0740 0.0437 0.1279 -0.2211 0.0538 12.6126 0.7152 15.0000 15.0000 13.8892 0.0924 0.0842 0.0998 10.7182 0.0714 0.0406 0.1179 -0.2320 0.0465 12.6783 0.6780 15.0000 15.0000 13.8078 0.0590 0.0741 0.0998 10.6639 0.0677 0.0365 0.1049 -0.2488 0.0372 12.7439 0.6277 15.0000 15.0000 13.6881 0.0126 0.0616 0.0999 10.6103 0.0627 0.0314 0.0886 -0.2729 0.0257 12.8096 0.5592 15.0000 15.0000 13.3568 -0.0521 0.0458 0.0999 10.5571 0.0559 0.0249 0.0680 -0.3069 0.0116 12.8753 0.4584 15.0000 15.0000 12.6487 -0.1487 0.0241 0.0999 10.5045 0.0458 0.0168 0.0406 -0.3585 -0.0062 12.9409 0.2597 15.0000 15.0000 12.8105 -0.3418 -0.0152 0.0999 10.4523 0.0260 0.0055 -0.0069 -0.4627 -0.0342 13.0000 0.0336 15.0000 15.0076 15.0076 -0.5623 -0.0586 0.1000 10.4110 0.0034 0.0000 -0.0586 0.0000 0.0000 RADIUS: 13.00 PROPELLER RADIUS (IN) HUBRAD: 0.88 HUB RADIUS (IN) HUBTRA: 3.38 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.476096 TOTAL WEIGHT (Kg) = 0.215916 TOTAL VOLUME (IN**3) = 7.756207 TOTAL PROJECTED AREA (IN**2) = 39.1579 MOMENT OF INERTIA (SNAIL-IN**2) = 0.036784 MOMENT OF INERTIA (Kg-M**2) = 0.004154 STATIC MOMENT, ONE SIDE (IN-LB) = 1.052312 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 = 73.130 INNER LIMIT (NORMALIZED BY RADIUS) = 0.067 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4153.14 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.38, E63 (Transition Start, Airfoil 1) AIRFOIL2: 7.49, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412