8.75x8.0NN (875x80NN.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 11.0861 -0.5000 -0.5000 0.4500 0.0000 0.2141 0.0000 0.1927 0.0000 0.2200 0.0000 0.0000 0.1200 0.8593 10.1760 -0.4851 -1.0057 0.4452 0.0072 0.2204 -32.7592 0.1894 0.3743 0.2221 0.0144 -0.0359 0.2400 0.8131 9.3848 -0.3840 -1.4856 0.4424 0.0263 0.2262 -14.2881 0.1839 0.3572 0.2275 0.0357 -0.0354 0.3600 0.7685 8.7055 -0.1172 -1.8067 0.4414 0.0537 0.2313 -2.9671 0.1777 0.3297 0.2344 0.0607 -0.0323 0.4800 0.7332 8.1313 0.3860 -1.8249 0.4416 0.0862 0.2358 7.2932 0.1729 0.2944 0.2418 0.0875 -0.0271 0.6000 0.7126 7.6551 1.1780 -1.4239 0.4429 0.1203 0.2397 17.3522 0.1708 0.2562 0.2492 0.1144 -0.0206 0.7200 0.7077 7.2700 2.2709 -0.5377 0.4447 0.1528 0.2430 26.6561 0.1720 0.2192 0.2559 0.1396 -0.0137 0.8400 0.7144 6.9689 3.6024 0.7983 0.4467 0.1806 0.2457 34.3151 0.1755 0.1863 0.2610 0.1612 -0.0072 0.9600 0.7249 6.7451 4.9957 2.3821 0.4487 0.2003 0.2477 39.6322 0.1796 0.1596 0.2632 0.1775 -0.0017 1.0800 0.7306 6.5914 6.1445 3.8036 0.4501 0.2087 0.2492 42.1603 0.1821 0.1401 0.2605 0.1868 0.0024 1.2000 0.7250 6.5010 6.6613 4.4923 0.4507 0.2025 0.2500 41.4600 0.1813 0.1288 0.2510 0.1878 0.0047 1.3188 0.7117 6.4669 6.6624 4.5668 0.4506 0.1868 0.2503 38.7992 0.1781 0.1203 0.2357 0.1844 0.0049 1.4178 0.7004 6.4758 6.6947 4.7531 0.4503 0.1743 0.2500 36.9252 0.1751 0.1100 0.2215 0.1834 0.0040 1.5156 0.6891 6.5137 6.7549 5.0056 0.4499 0.1625 0.2493 35.3496 0.1718 0.0992 0.2071 0.1834 0.0025 1.6134 0.6776 6.5769 6.8396 5.2833 0.4493 0.1514 0.2483 34.0075 0.1682 0.0897 0.1938 0.1839 0.0009 1.7112 0.6660 6.6615 6.9451 5.5604 0.4485 0.1409 0.2468 32.8604 0.1644 0.0827 0.1824 0.1846 -0.0005 1.8090 0.6542 6.7638 7.0677 5.8314 0.4475 0.1311 0.2449 31.8737 0.1602 0.0779 0.1730 0.1851 -0.0015 1.9068 0.6423 6.8801 7.2034 6.1090 0.4463 0.1218 0.2426 31.0162 0.1558 0.0745 0.1651 0.1857 -0.0022 2.0046 0.6301 7.0064 7.3486 6.4052 0.4448 0.1130 0.2399 30.2607 0.1512 0.0710 0.1576 0.1864 -0.0030 2.1024 0.6176 7.1392 7.4992 6.7086 0.4430 0.1047 0.2368 29.5835 0.1463 0.0675 0.1502 0.1874 -0.0041 2.2002 0.6048 7.2746 7.6515 7.0044 0.4409 0.0969 0.2333 28.9637 0.1411 0.0639 0.1428 0.1886 -0.0055 2.2980 0.5918 7.4088 7.8016 7.2749 0.4384 0.0895 0.2294 28.3831 0.1357 0.0602 0.1352 0.1900 -0.0071 2.3958 0.5783 7.5381 7.9455 7.5003 0.4357 0.0825 0.2251 27.8261 0.1302 0.0564 0.1274 0.1917 -0.0091 2.4936 0.5645 7.6587 8.0794 7.6597 0.4325 0.0759 0.2203 27.2785 0.1244 0.0527 0.1192 0.1937 -0.0115 2.5914 0.5502 7.7668 8.1992 7.7679 0.4290 0.0696 0.2154 26.7281 0.1185 0.0489 0.1109 0.1957 -0.0141 2.6892 0.5354 7.8588 8.3011 7.8598 0.4250 0.0635 0.2104 26.1640 0.1127 0.0452 0.1027 0.1975 -0.0165 2.7870 0.5201 7.9307 8.3812 7.9316 0.4206 0.0575 0.2055 25.5763 0.1069 0.0417 0.0948 0.1991 -0.0186 2.8848 0.5043 7.9789 8.4354 7.9797 0.4157 0.0517 0.2005 24.9561 0.1011 0.0382 0.0871 0.2004 -0.0205 2.9826 0.4878 7.9995 8.4597 8.0003 0.4104 0.0461 0.1956 24.2951 0.0954 0.0349 0.0796 0.2015 -0.0220 3.0804 0.4707 8.0000 8.4614 8.0007 0.4046 0.0407 0.1906 23.6135 0.0897 0.0317 0.0723 0.2024 -0.0234 3.1782 0.4530 8.0000 8.4598 8.0007 0.3982 0.0356 0.1857 22.9592 0.0841 0.0286 0.0652 0.2031 -0.0247 3.2760 0.4345 8.0000 8.4550 8.0006 0.3913 0.0306 0.1807 22.3308 0.0785 0.0256 0.0584 0.2035 -0.0258 3.3738 0.4152 8.0000 8.4467 8.0005 0.3838 0.0259 0.1757 21.7252 0.0730 0.0228 0.0517 0.2038 -0.0268 3.4716 0.3951 8.0000 8.4343 8.0005 0.3758 0.0214 0.1708 21.1396 0.0675 0.0201 0.0453 0.2039 -0.0278 3.5694 0.3742 8.0000 8.4171 8.0004 0.3671 0.0172 0.1658 20.5712 0.0621 0.0176 0.0391 0.2037 -0.0285 3.6672 0.3524 8.0000 8.3942 8.0003 0.3578 0.0131 0.1609 20.0167 0.0567 0.0152 0.0330 0.2032 -0.0292 3.7650 0.3297 8.0000 8.3644 8.0003 0.3479 0.0093 0.1559 19.4725 0.0514 0.0129 0.0272 0.2025 -0.0297 3.8628 0.3061 8.0000 8.3261 8.0002 0.3372 0.0056 0.1510 18.9344 0.0462 0.0108 0.0217 0.2015 -0.0301 3.9606 0.2814 8.0000 8.2767 8.0002 0.3259 0.0021 0.1460 18.3968 0.0411 0.0089 0.0163 0.2003 -0.0303 4.0584 0.2557 7.9708 8.1838 7.9710 0.3139 -0.0013 0.1411 17.7932 0.0361 0.0072 0.0111 0.1987 -0.0303 4.1523 0.2300 7.8021 7.9359 7.8021 0.3016 -0.0045 0.1363 16.9186 0.0314 0.0057 0.0064 0.1968 -0.0298 4.1783 0.2227 7.7286 7.8365 7.7286 0.2981 -0.0053 0.1350 16.6201 0.0301 0.0053 0.0051 0.1962 -0.0296 4.2004 0.2165 7.6572 7.7414 7.6572 0.2951 -0.0061 0.1339 16.3476 0.0290 0.0050 0.0040 0.1957 -0.0294 4.2225 0.2102 7.5774 7.6364 7.5774 0.2920 -0.0068 0.1327 16.0575 0.0279 0.0047 0.0030 0.1952 -0.0292 4.2446 0.2038 7.4893 7.5213 7.4893 0.2889 -0.0075 0.1316 15.7493 0.0268 0.0044 0.0019 0.1946 -0.0289 4.2667 0.1958 7.3929 7.3959 7.3929 0.2842 -0.0087 0.1305 15.4230 0.0255 0.0040 0.0003 0.1933 -0.0289 4.2888 0.1833 7.2882 7.2599 7.2919 0.2752 -0.0111 0.1294 15.0780 0.0237 0.0035 -0.0026 0.1897 -0.0297 4.3109 0.1651 7.1751 7.1129 7.2407 0.2608 -0.0149 0.1283 14.7137 0.0212 0.0028 -0.0073 0.1832 -0.0315 4.3330 0.1382 7.0537 6.9544 7.2653 0.2379 -0.0208 0.1271 14.3293 0.0176 0.0020 -0.0145 0.1722 -0.0346 4.3551 0.0877 6.9239 6.7840 7.7226 0.1922 -0.0325 0.1260 13.9238 0.0111 0.0008 -0.0285 0.1492 -0.0414 4.3750 0.0083 6.8000 6.8001 6.8000 0.1180 -0.0511 0.1250 13.8946 0.0010 0.0000 -0.0511 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) = 0.056140 TOTAL WEIGHT (Kg) = 0.025460 TOTAL VOLUME (IN**3) = 0.914590 TOTAL PROJECTED AREA (IN**2) = 4.3134 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000278 MOMENT OF INERTIA (Kg-M**2) = 0.000031 STATIC MOMENT, ONE SIDE (IN-LB) = 0.028944 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 = 65.994 INNER LIMIT (NORMALIZED BY RADIUS) = 0.103 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 39037.52 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.