8.8x8.75 (88x875.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 0.9000 7.3145 -0.5000 -0.5000 0.4500 0.0000 0.2487 0.0000 0.2238 0.0000 0.2100 0.0000 0.0000 0.1200 0.8597 7.0085 -0.4851 -1.0235 0.4452 0.0069 0.2533 -32.7585 0.2178 0.3744 0.2124 0.0139 -0.0447 0.2400 0.8143 6.7662 -0.3840 -1.5175 0.4424 0.0252 0.2574 -14.2865 0.2096 0.3580 0.2186 0.0348 -0.0437 0.3600 0.7708 6.5833 -0.1183 -1.8495 0.4414 0.0515 0.2609 -2.9949 0.2011 0.3317 0.2269 0.0592 -0.0394 0.4800 0.7363 6.4553 0.3812 -1.8780 0.4416 0.0827 0.2639 7.2042 0.1943 0.2978 0.2363 0.0853 -0.0322 0.6000 0.7161 6.3780 1.1670 -1.4891 0.4429 0.1154 0.2663 17.2007 0.1907 0.2610 0.2457 0.1117 -0.0235 0.7200 0.7113 6.3470 2.2548 -0.6170 0.4447 0.1468 0.2682 26.4930 0.1907 0.2250 0.2541 0.1366 -0.0146 0.8400 0.7177 6.3579 3.5924 0.7084 0.4467 0.1736 0.2695 34.2413 0.1934 0.1927 0.2603 0.1584 -0.0065 0.9600 0.7280 6.4063 5.0221 2.3012 0.4487 0.1927 0.2702 39.7807 0.1967 0.1661 0.2630 0.1755 -0.0001 1.0800 0.7335 6.4879 6.2598 3.7733 0.4501 0.2011 0.2704 42.6907 0.1983 0.1463 0.2606 0.1864 0.0037 1.2000 0.7272 6.5983 6.9269 4.5636 0.4507 0.1956 0.2700 42.5738 0.1963 0.1344 0.2511 0.1899 0.0043 1.3189 0.7124 6.7318 7.0943 4.7588 0.4506 0.1810 0.2691 40.5672 0.1917 0.1251 0.2358 0.1893 0.0023 1.4181 0.6998 6.8587 7.2447 5.0403 0.4503 0.1694 0.2679 39.1133 0.1875 0.1141 0.2215 0.1902 -0.0001 1.5163 0.6872 6.9952 7.4039 5.3843 0.4499 0.1585 0.2663 37.8528 0.1830 0.1027 0.2072 0.1918 -0.0026 1.6144 0.6746 7.1404 7.5711 5.7487 0.4493 0.1482 0.2644 36.7377 0.1783 0.0926 0.1939 0.1935 -0.0048 1.7125 0.6618 7.2919 7.7438 6.1032 0.4485 0.1384 0.2621 35.7419 0.1734 0.0850 0.1824 0.1949 -0.0065 1.8106 0.6489 7.4474 7.9195 6.4396 0.4475 0.1291 0.2594 34.8424 0.1683 0.0796 0.1731 0.1958 -0.0075 1.9088 0.6360 7.6043 8.0956 6.7710 0.4463 0.1202 0.2563 34.0198 0.1630 0.0757 0.1651 0.1966 -0.0080 2.0069 0.6230 7.7604 8.2695 7.1118 0.4447 0.1118 0.2529 33.2570 0.1576 0.0718 0.1575 0.1973 -0.0085 2.1050 0.6100 7.9133 8.4389 7.4507 0.4429 0.1038 0.2491 32.5393 0.1519 0.0679 0.1500 0.1982 -0.0093 2.2032 0.5968 8.0605 8.6010 7.7726 0.4408 0.0962 0.2449 31.8539 0.1462 0.0640 0.1426 0.1991 -0.0103 2.3013 0.5836 8.1997 8.7533 8.0594 0.4383 0.0890 0.2404 31.1895 0.1403 0.0602 0.1350 0.2002 -0.0117 2.3994 0.5703 8.3285 8.8934 8.2910 0.4355 0.0821 0.2354 30.5364 0.1343 0.0564 0.1271 0.2014 -0.0135 2.4976 0.5569 8.4446 9.0185 8.4464 0.4324 0.0755 0.2301 29.8858 0.1282 0.0526 0.1189 0.2028 -0.0158 2.5957 0.5435 8.5455 9.1265 8.5471 0.4288 0.0692 0.2246 29.2310 0.1221 0.0489 0.1105 0.2040 -0.0184 2.6938 0.5299 8.6288 9.2154 8.6303 0.4248 0.0630 0.2191 28.5666 0.1161 0.0454 0.1024 0.2050 -0.0208 2.7919 0.5163 8.6923 9.2828 8.6936 0.4204 0.0570 0.2137 27.8863 0.1103 0.0420 0.0944 0.2055 -0.0231 2.8901 0.5025 8.7334 9.3262 8.7346 0.4155 0.0512 0.2082 27.1846 0.1046 0.0388 0.0867 0.2056 -0.0251 2.9882 0.4887 8.7498 9.3433 8.7509 0.4101 0.0455 0.2027 26.4565 0.0990 0.0357 0.0792 0.2053 -0.0270 3.0863 0.4747 8.7500 9.3425 8.7510 0.4042 0.0400 0.1972 25.7234 0.0936 0.0328 0.0719 0.2046 -0.0288 3.1845 0.4606 8.7500 9.3399 8.7509 0.3978 0.0347 0.1917 25.0231 0.0883 0.0301 0.0648 0.2035 -0.0306 3.2826 0.4463 8.7500 9.3358 8.7508 0.3908 0.0296 0.1862 24.3536 0.0831 0.0274 0.0579 0.2019 -0.0323 3.3807 0.4320 8.7500 9.3300 8.7507 0.3833 0.0247 0.1807 23.7126 0.0780 0.0250 0.0513 0.1999 -0.0340 3.4788 0.4174 8.7500 9.3225 8.7505 0.3752 0.0200 0.1752 23.0982 0.0731 0.0226 0.0448 0.1975 -0.0356 3.5770 0.4028 8.7500 9.3133 8.7504 0.3664 0.0154 0.1697 22.5086 0.0684 0.0204 0.0386 0.1945 -0.0372 3.6751 0.3880 8.7500 9.3056 8.7444 0.3570 0.0112 0.1642 21.9489 0.0637 0.0184 0.0326 0.1909 -0.0387 3.7732 0.3733 8.7500 9.3373 8.6895 0.3470 0.0076 0.1587 21.4969 0.0592 0.0164 0.0269 0.1869 -0.0404 3.8714 0.3588 8.7500 9.4391 8.6045 0.3363 0.0052 0.1532 21.2086 0.0550 0.0146 0.0219 0.1822 -0.0420 3.9695 0.3445 8.7500 9.6332 8.5200 0.3248 0.0039 0.1477 21.1184 0.0509 0.0130 0.0179 0.1769 -0.0433 4.0676 0.3303 8.7073 9.8944 8.4217 0.3127 0.0038 0.1422 21.1635 0.0470 0.0114 0.0150 0.1710 -0.0441 4.1618 0.3168 8.5057 10.0957 8.2178 0.3003 0.0045 0.1369 21.1105 0.0434 0.0100 0.0134 0.1645 -0.0439 4.1879 0.3125 8.4205 10.1420 8.1435 0.2963 0.0046 0.1355 21.0784 0.0423 0.0096 0.0129 0.1622 -0.0438 4.2100 0.3063 8.3382 10.1787 8.0755 0.2905 0.0038 0.1342 21.0463 0.0411 0.0091 0.0115 0.1591 -0.0442 4.2322 0.2973 8.2468 10.2127 8.0029 0.2820 0.0019 0.1330 21.0097 0.0395 0.0085 0.0091 0.1544 -0.0451 4.2543 0.2851 8.1463 10.2440 7.9406 0.2704 -0.0011 0.1318 20.9682 0.0376 0.0077 0.0054 0.1481 -0.0467 4.2765 0.2690 8.0366 10.2725 7.8889 0.2553 -0.0055 0.1305 20.9221 0.0351 0.0068 0.0003 0.1397 -0.0490 4.2986 0.2478 7.9177 10.2977 7.8500 0.2353 -0.0117 0.1293 20.8703 0.0320 0.0057 -0.0066 0.1287 -0.0523 4.3208 0.2190 7.7897 10.3197 7.8404 0.2083 -0.0207 0.1280 20.8130 0.0280 0.0044 -0.0165 0.1139 -0.0570 4.3429 0.1753 7.6525 10.3386 7.9238 0.1674 -0.0351 0.1268 20.7506 0.0222 0.0028 -0.0319 0.0914 -0.0646 4.3651 0.0938 7.5061 10.3569 8.6164 0.0913 -0.0633 0.1256 20.6876 0.0118 0.0008 -0.0617 0.0497 -0.0796 4.3850 0.0138 7.3666 7.3666 7.3666 0.0169 -0.0924 0.1244 14.9693 0.0017 0.0000 -0.0924 0.0000 0.0000 RADIUS: 4.39 PROPELLER RADIUS (IN) HUBRAD: 0.45 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.057568 TOTAL WEIGHT (Kg) = 0.026108 TOTAL VOLUME (IN**3) = 0.937862 TOTAL PROJECTED AREA (IN**2) = 4.3433 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000300 MOMENT OF INERTIA (Kg-M**2) = 0.000034 STATIC MOMENT, ONE SIDE (IN-LB) = 0.030414 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 = 73.083 INNER LIMIT (NORMALIZED BY RADIUS) = 0.103 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 37514.19 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.