15.75x13-3 (1575x13-3.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) 0.0025 1.2817 -5.9749 0.0000 -0.0072 0.6409 0.0000 0.3429 0.0000 0.4394 0.0000 0.1800 0.0000 0.0000 0.1796 1.1452 -3.6437 0.0185 -0.5663 0.6140 0.0105 0.3404 0.9384 0.3898 0.4676 0.1874 0.0356 -0.0503 0.3563 1.0349 -1.4700 0.1517 -1.1497 0.5921 0.0395 0.3333 3.8757 0.3449 0.4348 0.2077 0.0680 -0.0399 0.5317 0.9533 0.5373 0.5174 -1.5453 0.5747 0.0826 0.3215 8.8042 0.3065 0.4040 0.2377 0.0953 -0.0227 0.7049 0.9037 2.3729 1.2153 -1.5597 0.5614 0.1360 0.3061 15.3444 0.2766 0.3757 0.2749 0.1179 0.0001 0.8752 0.8874 4.0349 2.2983 -1.0860 0.5516 0.1956 0.2910 22.6821 0.2583 0.3506 0.3169 0.1363 0.0265 1.0420 0.9009 5.5259 3.7489 -0.0802 0.5449 0.2572 0.2771 29.7953 0.2496 0.3286 0.3612 0.1510 0.0537 1.2051 0.9357 6.8523 5.4714 1.3747 0.5409 0.3169 0.2641 35.8526 0.2471 0.3091 0.4052 0.1625 0.0797 1.3646 0.9807 8.0251 7.3040 3.0734 0.5391 0.3706 0.2521 40.4262 0.2472 0.2918 0.4459 0.1709 0.1031 1.5217 1.0242 9.0584 9.0452 4.7983 0.5389 0.4143 0.2409 43.4116 0.2467 0.2768 0.4799 0.1756 0.1240 1.6840 1.0590 9.9998 10.4557 6.3649 0.5412 0.4438 0.2300 44.6592 0.2436 0.2662 0.5038 0.1749 0.1424 1.8537 1.0930 10.8472 11.3492 7.5423 0.5484 0.4566 0.2194 44.2570 0.2398 0.2608 0.5137 0.1690 0.1520 2.0465 1.1278 11.6394 12.1824 8.7930 0.5565 0.4527 0.2082 43.4533 0.2348 0.2525 0.5070 0.1613 0.1475 2.2406 1.1588 12.2543 12.8317 9.9181 0.5642 0.4443 0.1979 42.3480 0.2293 0.2425 0.4963 0.1526 0.1418 2.4347 1.1857 12.6856 13.2906 10.8662 0.5714 0.4353 0.1886 40.9842 0.2237 0.2315 0.4854 0.1433 0.1382 2.6288 1.2085 12.9335 13.5599 11.6026 0.5779 0.4255 0.1803 39.3845 0.2179 0.2202 0.4742 0.1335 0.1367 2.8229 1.2273 13.0000 13.6425 12.1019 0.5837 0.4149 0.1730 37.5663 0.2123 0.2092 0.4628 0.1233 0.1371 3.0170 1.2420 13.0000 13.6568 12.4542 0.5887 0.4038 0.1666 35.7704 0.2070 0.1991 0.4512 0.1141 0.1379 3.2111 1.2527 13.0000 13.6714 12.7192 0.5927 0.3922 0.1613 34.1220 0.2020 0.1905 0.4394 0.1065 0.1379 3.4052 1.2595 13.0000 13.6871 12.8969 0.5956 0.3802 0.1569 32.6079 0.1976 0.1836 0.4273 0.1004 0.1372 3.5993 1.2625 13.0000 13.7046 12.9875 0.5974 0.3677 0.1535 31.2158 0.1938 0.1786 0.4151 0.0955 0.1355 3.7934 1.2618 13.0000 13.7247 13.0000 0.5979 0.3547 0.1511 29.9348 0.1907 0.1752 0.4026 0.0917 0.1329 3.9875 1.2573 13.0000 13.7477 13.0002 0.5969 0.3411 0.1496 28.7545 0.1881 0.1721 0.3898 0.0885 0.1299 4.1816 1.2493 13.0000 13.7709 13.0004 0.5945 0.3274 0.1484 27.6605 0.1854 0.1685 0.3769 0.0856 0.1266 4.3757 1.2377 13.0000 13.7929 13.0005 0.5904 0.3137 0.1472 26.6422 0.1821 0.1639 0.3637 0.0830 0.1231 4.5698 1.2227 13.0000 13.8139 13.0004 0.5846 0.3000 0.1459 25.6925 0.1784 0.1586 0.3502 0.0804 0.1194 4.7639 1.2043 13.0000 13.8341 13.0004 0.5769 0.2862 0.1447 24.8055 0.1742 0.1526 0.3366 0.0777 0.1154 4.9580 1.1825 13.0000 13.8539 13.0003 0.5673 0.2725 0.1435 23.9757 0.1696 0.1459 0.3227 0.0748 0.1113 5.1521 1.1574 13.0000 13.8729 13.0003 0.5555 0.2587 0.1422 23.1978 0.1646 0.1386 0.3085 0.0715 0.1069 5.3462 1.1291 13.0000 13.8913 13.0003 0.5417 0.2450 0.1410 22.4672 0.1592 0.1308 0.2942 0.0676 0.1023 5.5403 1.0976 13.0000 13.9089 13.0002 0.5255 0.2312 0.1397 21.7796 0.1534 0.1226 0.2795 0.0630 0.0975 5.7344 1.0630 13.0000 13.9255 13.0002 0.5069 0.2174 0.1385 21.1313 0.1472 0.1140 0.2647 0.0576 0.0925 5.9285 1.0254 13.0000 13.9410 13.0002 0.4857 0.2036 0.1373 20.5188 0.1408 0.1052 0.2496 0.0510 0.0872 6.1226 0.9847 13.0000 13.9554 13.0001 0.4620 0.1898 0.1360 19.9391 0.1340 0.0962 0.2343 0.0433 0.0816 6.3167 0.9411 13.0000 13.9683 13.0001 0.4355 0.1759 0.1348 19.3894 0.1269 0.0871 0.2187 0.0343 0.0759 6.5108 0.8946 13.0000 13.9797 13.0001 0.4062 0.1620 0.1336 18.8670 0.1195 0.0781 0.2029 0.0237 0.0699 6.7049 0.8454 13.0000 13.9892 13.0001 0.3738 0.1480 0.1323 18.3695 0.1119 0.0691 0.1868 0.0116 0.0636 6.8990 0.7933 12.9591 13.9551 12.9591 0.3385 0.1339 0.1311 17.8453 0.1040 0.0604 0.1705 -0.0024 0.0573 7.0931 0.7385 12.8034 13.8030 12.8035 0.2999 0.1195 0.1299 17.2084 0.0959 0.0519 0.1540 -0.0185 0.0513 7.2872 0.6811 12.5316 13.5307 12.5316 0.2580 0.1049 0.1286 16.4633 0.0876 0.0438 0.1372 -0.0367 0.0453 7.4732 0.6237 12.1620 13.1562 12.1620 0.2147 0.0907 0.1274 15.6520 0.0795 0.0364 0.1209 -0.0563 0.0395 7.5210 0.6075 12.0497 13.0421 12.0501 0.2020 0.0868 0.1271 15.4289 0.0772 0.0345 0.1164 -0.0622 0.0378 7.5608 0.5897 11.9510 12.9426 11.9527 0.1873 0.0824 0.1269 15.2399 0.0748 0.0325 0.1113 -0.0695 0.0356 7.6006 0.5671 11.8474 12.8389 11.8513 0.1678 0.0769 0.1266 15.0479 0.0718 0.0300 0.1048 -0.0794 0.0326 7.6403 0.5389 11.7389 12.7307 11.7494 0.1428 0.0700 0.1264 14.8525 0.0681 0.0270 0.0966 -0.0923 0.0286 7.6801 0.5038 11.6255 12.6178 11.6520 0.1111 0.0614 0.1261 14.6536 0.0635 0.0236 0.0865 -0.1090 0.0234 7.7199 0.4595 11.5073 12.5002 11.5587 0.0704 0.0508 0.1259 14.4510 0.0578 0.0196 0.0738 -0.1307 0.0167 7.7597 0.4010 11.3842 12.3776 11.4785 0.0159 0.0369 0.1256 14.2448 0.0504 0.0149 0.0571 -0.1601 0.0076 7.7994 0.3133 11.2562 12.2513 11.4488 -0.0672 0.0163 0.1254 14.0362 0.0393 0.0091 0.0322 -0.2052 -0.0063 7.8392 0.1637 11.1233 12.1261 11.7360 -0.2105 -0.0185 0.1251 13.8306 0.0205 0.0025 -0.0102 -0.2837 -0.0304 7.8750 0.0245 10.9995 10.9996 10.9995 -0.3441 -0.0507 0.1249 12.5332 0.0031 0.0000 -0.0507 0.0000 0.0000 RADIUS: 7.88 PROPELLER RADIUS (IN) HUBRAD: 0.70 HUB RADIUS (IN) HUBTRA: 1.68 HUB TRANSITION (IN) BLADES: 3 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.249874 TOTAL WEIGHT (Kg) = 0.113322 TOTAL VOLUME (IN**3) = 4.070773 TOTAL PROJECTED AREA (IN**2) = 20.4854 MOMENT OF INERTIA (SNAIL-IN**2) = 0.007777 MOMENT OF INERTIA (Kg-M**2) = 0.000878 STATIC MOMENT, ONE SIDE (IN-LB) = 0.241283 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 = 87.194 INNER LIMIT (NORMALIZED BY RADIUS) = 0.089 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 11020.42 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.78, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 2.67, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.