8.75x9.0W (875x90W.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 11.0385 -0.5000 -0.5000 0.4500 0.0000 0.2017 0.0000 0.1815 0.0000 0.2100 0.0000 0.0000 0.1200 0.8592 10.1277 -0.4850 -1.0229 0.4452 0.0072 0.2098 -32.7519 0.1803 0.3742 0.2124 0.0141 -0.0447 0.2400 0.8128 9.3460 -0.3829 -1.5195 0.4424 0.0263 0.2172 -14.2466 0.1765 0.3573 0.2185 0.0356 -0.0437 0.3600 0.7679 8.6855 -0.1129 -1.8543 0.4414 0.0539 0.2238 -2.8578 0.1719 0.3299 0.2265 0.0608 -0.0399 0.4800 0.7325 8.1385 0.3975 -1.8798 0.4416 0.0863 0.2298 7.5091 0.1683 0.2947 0.2353 0.0879 -0.0338 0.6000 0.7119 7.6971 1.2038 -1.4754 0.4429 0.1206 0.2350 17.7091 0.1673 0.2566 0.2442 0.1151 -0.0263 0.7200 0.7074 7.3535 2.3222 -0.5699 0.4447 0.1533 0.2394 27.1723 0.1694 0.2196 0.2524 0.1407 -0.0186 0.8400 0.7147 7.0998 3.6947 0.8064 0.4467 0.1812 0.2432 34.9933 0.1738 0.1868 0.2589 0.1627 -0.0115 0.9600 0.7259 6.9283 5.1471 2.4527 0.4487 0.2011 0.2462 40.4746 0.1787 0.1601 0.2622 0.1796 -0.0056 1.0800 0.7321 6.8311 6.3685 3.9502 0.4501 0.2096 0.2484 43.1828 0.1819 0.1407 0.2603 0.1896 -0.0015 1.2000 0.7263 6.8004 6.9570 4.7045 0.4507 0.2037 0.2500 42.6979 0.1816 0.1295 0.2511 0.1912 0.0004 1.3188 0.7121 6.8278 7.0201 4.8275 0.4506 0.1882 0.2508 40.2703 0.1786 0.1210 0.2359 0.1885 0.0000 1.4178 0.7001 6.8891 7.1051 5.0624 0.4503 0.1759 0.2509 38.5753 0.1757 0.1106 0.2217 0.1880 -0.0013 1.5156 0.6881 6.9794 7.2180 5.3694 0.4499 0.1643 0.2506 37.1610 0.1724 0.0996 0.2075 0.1885 -0.0031 1.6134 0.6759 7.0950 7.3554 5.7056 0.4493 0.1535 0.2497 35.9639 0.1688 0.0900 0.1943 0.1895 -0.0050 1.7112 0.6637 7.2317 7.5133 6.0424 0.4485 0.1432 0.2484 34.9454 0.1649 0.0827 0.1828 0.1905 -0.0066 1.8090 0.6513 7.3852 7.6872 6.3727 0.4475 0.1335 0.2466 34.0711 0.1606 0.0778 0.1734 0.1913 -0.0077 1.9068 0.6388 7.5514 7.8730 6.7097 0.4463 0.1244 0.2443 33.3104 0.1561 0.0742 0.1655 0.1919 -0.0084 2.0046 0.6262 7.7259 8.0664 7.0663 0.4448 0.1158 0.2415 32.6367 0.1512 0.0706 0.1578 0.1928 -0.0093 2.1024 0.6134 7.9045 8.2630 7.4299 0.4430 0.1076 0.2383 32.0268 0.1461 0.0670 0.1503 0.1938 -0.0104 2.2002 0.6004 8.0830 8.4585 7.7840 0.4409 0.1000 0.2345 31.4606 0.1408 0.0633 0.1429 0.1949 -0.0117 2.2980 0.5873 8.2572 8.6485 8.1085 0.4384 0.0927 0.2303 30.9204 0.1352 0.0596 0.1353 0.1962 -0.0133 2.3958 0.5740 8.4228 8.8285 8.3808 0.4357 0.0858 0.2256 30.3908 0.1295 0.0558 0.1274 0.1976 -0.0152 2.4936 0.5604 8.5756 8.9942 8.5769 0.4325 0.0792 0.2204 29.8582 0.1235 0.0519 0.1192 0.1993 -0.0176 2.5914 0.5467 8.7114 9.1412 8.7127 0.4290 0.0729 0.2149 29.3106 0.1175 0.0482 0.1109 0.2010 -0.0201 2.6892 0.5326 8.8259 9.2651 8.8271 0.4250 0.0668 0.2094 28.7374 0.1115 0.0446 0.1028 0.2024 -0.0225 2.7870 0.5183 8.9149 9.3615 8.9160 0.4206 0.0608 0.2039 28.1288 0.1057 0.0411 0.0948 0.2034 -0.0246 2.8848 0.5036 8.9741 9.4260 8.9752 0.4157 0.0550 0.1984 27.4757 0.0999 0.0378 0.0871 0.2041 -0.0264 2.9826 0.4887 8.9994 9.4541 9.0003 0.4104 0.0493 0.1930 26.7699 0.0943 0.0346 0.0796 0.2043 -0.0280 3.0804 0.4733 9.0000 9.4550 9.0009 0.4046 0.0437 0.1875 26.0359 0.0887 0.0315 0.0723 0.2042 -0.0294 3.1782 0.4576 9.0000 9.4526 9.0008 0.3982 0.0384 0.1820 25.3307 0.0833 0.0286 0.0652 0.2038 -0.0307 3.2760 0.4416 9.0000 9.4472 9.0007 0.3913 0.0333 0.1765 24.6533 0.0780 0.0259 0.0584 0.2031 -0.0320 3.3738 0.4251 9.0000 9.4386 9.0006 0.3838 0.0284 0.1711 24.0009 0.0727 0.0233 0.0517 0.2020 -0.0332 3.4716 0.4081 9.0000 9.4263 9.0005 0.3758 0.0237 0.1656 23.3712 0.0676 0.0208 0.0453 0.2005 -0.0344 3.5694 0.3908 9.0000 9.4100 9.0004 0.3671 0.0192 0.1601 22.7616 0.0626 0.0185 0.0391 0.1986 -0.0354 3.6672 0.3729 9.0000 9.3890 9.0003 0.3578 0.0148 0.1546 22.1697 0.0577 0.0163 0.0331 0.1963 -0.0364 3.7650 0.3546 9.0000 9.3629 9.0003 0.3479 0.0107 0.1492 21.5929 0.0529 0.0143 0.0273 0.1936 -0.0374 3.8628 0.3357 9.0000 9.3306 9.0002 0.3372 0.0067 0.1437 21.0284 0.0482 0.0124 0.0217 0.1904 -0.0382 3.9606 0.3163 9.0000 9.2910 9.0002 0.3259 0.0029 0.1382 20.4732 0.0437 0.0106 0.0163 0.1867 -0.0389 4.0584 0.2964 8.9757 9.2185 8.9758 0.3139 -0.0008 0.1327 19.8754 0.0393 0.0090 0.0111 0.1825 -0.0395 4.1523 0.2767 8.8351 9.0219 8.8351 0.3016 -0.0043 0.1275 19.0755 0.0353 0.0076 0.0064 0.1778 -0.0395 4.1783 0.2712 8.7738 8.9432 8.7739 0.2981 -0.0052 0.1260 18.8114 0.0342 0.0073 0.0051 0.1764 -0.0395 4.2004 0.2664 8.7143 8.8681 8.7143 0.2951 -0.0061 0.1248 18.5731 0.0332 0.0070 0.0040 0.1752 -0.0394 4.2225 0.2602 8.6478 8.7856 8.6480 0.2906 -0.0073 0.1235 18.3219 0.0321 0.0066 0.0024 0.1732 -0.0396 4.2446 0.2507 8.5744 8.6954 8.5748 0.2831 -0.0096 0.1223 18.0580 0.0307 0.0061 -0.0003 0.1696 -0.0404 4.2667 0.2375 8.4941 8.5976 8.5047 0.2720 -0.0131 0.1211 17.7812 0.0288 0.0054 -0.0043 0.1641 -0.0419 4.2888 0.2198 8.4068 8.4920 8.4584 0.2565 -0.0179 0.1198 17.4912 0.0263 0.0046 -0.0098 0.1562 -0.0444 4.3109 0.1955 8.3126 8.3784 8.4389 0.2349 -0.0246 0.1186 17.1879 0.0232 0.0036 -0.0174 0.1450 -0.0479 4.3330 0.1600 8.2114 8.2567 8.5008 0.2024 -0.0345 0.1174 16.8713 0.0188 0.0024 -0.0287 0.1280 -0.0536 4.3551 0.0902 8.1033 8.1271 9.1253 0.1371 -0.0543 0.1161 16.5414 0.0105 0.0008 -0.0511 0.0935 -0.0655 4.3750 0.0114 8.0000 8.0000 8.0000 0.0629 -0.0764 0.1150 16.2264 0.0013 0.0000 -0.0764 0.0000 0.0000 RADIUS: 4.38 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) = 0.056303 TOTAL WEIGHT (Kg) = 0.025534 TOTAL VOLUME (IN**3) = 0.917241 TOTAL PROJECTED AREA (IN**2) = 4.2964 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000283 MOMENT OF INERTIA (Kg-M**2) = 0.000032 STATIC MOMENT, ONE SIDE (IN-LB) = 0.029207 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 = 70.163 INNER LIMIT (NORMALIZED BY RADIUS) = 0.103 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 37672.56 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.