8.75x9.0NN (875x90NN.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 7.2234 -0.5000 -0.5000 0.4500 0.0000 0.2141 0.0000 0.1927 0.0000 0.2000 0.0000 0.0000 0.1200 0.8595 6.9634 -0.4855 -1.0397 0.4452 0.0071 0.2204 -32.7756 0.1895 0.3739 0.2026 0.0137 -0.0532 0.2400 0.8138 6.7628 -0.3863 -1.5517 0.4424 0.0261 0.2262 -14.3696 0.1840 0.3568 0.2096 0.0348 -0.0511 0.3600 0.7695 6.6176 -0.1243 -1.8999 0.4414 0.0534 0.2313 -3.1455 0.1780 0.3293 0.2187 0.0596 -0.0457 0.4800 0.7342 6.5235 0.3710 -1.9379 0.4416 0.0857 0.2358 7.0129 0.1731 0.2941 0.2289 0.0862 -0.0378 0.6000 0.7130 6.4764 1.1535 -1.5468 0.4429 0.1197 0.2397 17.0122 0.1709 0.2561 0.2393 0.1131 -0.0285 0.7200 0.7074 6.4722 2.2409 -0.6562 0.4447 0.1523 0.2430 26.3515 0.1719 0.2192 0.2490 0.1385 -0.0191 0.8400 0.7134 6.5067 3.5831 0.7065 0.4467 0.1802 0.2457 34.1723 0.1753 0.1863 0.2568 0.1607 -0.0106 0.9600 0.7238 6.5757 5.0232 2.3516 0.4487 0.2003 0.2477 39.7868 0.1793 0.1596 0.2611 0.1780 -0.0039 1.0800 0.7298 6.6750 6.2752 3.8785 0.4501 0.2092 0.2492 42.7613 0.1819 0.1401 0.2600 0.1889 0.0002 1.2000 0.7245 6.8006 6.9571 4.7050 0.4507 0.2038 0.2500 42.6981 0.1812 0.1289 0.2511 0.1918 0.0009 1.3188 0.7110 6.9466 7.1368 4.9134 0.4506 0.1889 0.2503 40.7367 0.1779 0.1205 0.2360 0.1903 -0.0011 1.4178 0.6996 7.0819 7.2951 5.2069 0.4503 0.1771 0.2500 39.3142 0.1749 0.1102 0.2219 0.1904 -0.0034 1.5156 0.6883 7.2252 7.4606 5.5622 0.4499 0.1658 0.2493 38.0768 0.1716 0.0994 0.2078 0.1911 -0.0059 1.6134 0.6768 7.3759 7.6331 5.9358 0.4493 0.1551 0.2483 36.9785 0.1680 0.0898 0.1946 0.1920 -0.0082 1.7112 0.6652 7.5318 7.8101 6.2974 0.4485 0.1449 0.2468 35.9947 0.1642 0.0826 0.1832 0.1927 -0.0100 1.8090 0.6535 7.6905 7.9895 6.6398 0.4475 0.1352 0.2449 35.1038 0.1600 0.0778 0.1737 0.1931 -0.0112 1.9068 0.6415 7.8499 8.1689 6.9776 0.4463 0.1260 0.2426 34.2875 0.1556 0.0744 0.1656 0.1933 -0.0119 2.0046 0.6294 8.0076 8.3460 7.3256 0.4448 0.1172 0.2399 33.5296 0.1510 0.0709 0.1579 0.1936 -0.0126 2.1024 0.6170 8.1614 8.5184 7.6722 0.4430 0.1088 0.2368 32.8161 0.1461 0.0674 0.1504 0.1941 -0.0134 2.2002 0.6043 8.3091 8.6838 8.0021 0.4409 0.1009 0.2333 32.1349 0.1410 0.0638 0.1429 0.1947 -0.0144 2.2980 0.5913 8.4484 8.8396 8.2964 0.4384 0.0933 0.2294 31.4754 0.1356 0.0601 0.1353 0.1956 -0.0157 2.3958 0.5779 8.5771 8.9836 8.5343 0.4357 0.0862 0.2251 30.8281 0.1301 0.0564 0.1275 0.1969 -0.0173 2.4936 0.5641 8.6929 9.1133 8.6941 0.4325 0.0793 0.2203 30.1847 0.1243 0.0526 0.1193 0.1984 -0.0193 2.5914 0.5499 8.7935 9.2263 8.7948 0.4290 0.0728 0.2154 29.5377 0.1184 0.0488 0.1109 0.2001 -0.0216 2.6892 0.5351 8.8767 9.3200 8.8780 0.4250 0.0665 0.2104 28.8803 0.1126 0.0452 0.1028 0.2015 -0.0236 2.7870 0.5199 8.9403 9.3921 8.9415 0.4206 0.0603 0.2055 28.2065 0.1068 0.0416 0.0948 0.2028 -0.0253 2.8848 0.5041 8.9820 9.4401 8.9831 0.4157 0.0544 0.2005 27.5107 0.1011 0.0382 0.0871 0.2039 -0.0269 2.9826 0.4877 8.9996 9.4615 9.0006 0.4104 0.0486 0.1956 26.7879 0.0954 0.0349 0.0796 0.2047 -0.0281 3.0804 0.4706 9.0000 9.4631 9.0009 0.4046 0.0431 0.1906 26.0552 0.0897 0.0317 0.0723 0.2053 -0.0292 3.1782 0.4528 9.0000 9.4615 9.0008 0.3982 0.0378 0.1857 25.3515 0.0841 0.0286 0.0652 0.2057 -0.0302 3.2760 0.4343 9.0000 9.4566 9.0008 0.3913 0.0327 0.1807 24.6749 0.0785 0.0256 0.0584 0.2060 -0.0311 3.3738 0.4151 9.0000 9.4481 9.0006 0.3838 0.0278 0.1757 24.0224 0.0730 0.0228 0.0517 0.2061 -0.0318 3.4716 0.3950 9.0000 9.4353 9.0005 0.3758 0.0232 0.1708 23.3912 0.0675 0.0201 0.0453 0.2059 -0.0325 3.5694 0.3741 9.0000 9.4177 9.0004 0.3671 0.0188 0.1658 22.7785 0.0620 0.0176 0.0391 0.2055 -0.0330 3.6672 0.3524 9.0000 9.3944 9.0004 0.3578 0.0146 0.1609 22.1810 0.0567 0.0152 0.0330 0.2049 -0.0333 3.7650 0.3297 9.0000 9.3639 9.0003 0.3479 0.0106 0.1559 21.5952 0.0514 0.0129 0.0272 0.2041 -0.0336 3.8628 0.3060 9.0000 9.3248 9.0002 0.3372 0.0068 0.1510 21.0165 0.0462 0.0108 0.0217 0.2029 -0.0336 3.9606 0.2814 9.0000 9.2745 9.0002 0.3259 0.0032 0.1460 20.4397 0.0411 0.0089 0.0163 0.2015 -0.0336 4.0584 0.2557 8.9672 9.1766 8.9673 0.3139 -0.0003 0.1411 19.7922 0.0361 0.0072 0.0111 0.1998 -0.0333 4.1523 0.2300 8.7773 8.9062 8.7774 0.3016 -0.0036 0.1363 18.8483 0.0314 0.0057 0.0064 0.1977 -0.0324 4.1783 0.2227 8.6946 8.7972 8.6947 0.2981 -0.0045 0.1350 18.5254 0.0301 0.0053 0.0051 0.1971 -0.0321 4.2004 0.2165 8.6143 8.6929 8.6143 0.2951 -0.0053 0.1339 18.2305 0.0290 0.0050 0.0040 0.1965 -0.0318 4.2225 0.2102 8.5246 8.5775 8.5246 0.2920 -0.0061 0.1327 17.9161 0.0279 0.0047 0.0030 0.1960 -0.0315 4.2446 0.2038 8.4255 8.4511 8.4255 0.2889 -0.0068 0.1316 17.5822 0.0268 0.0044 0.0019 0.1954 -0.0312 4.2667 0.1959 8.3170 8.3132 8.3170 0.2843 -0.0080 0.1305 17.2284 0.0256 0.0040 0.0003 0.1940 -0.0311 4.2888 0.1835 8.1992 8.1637 8.1990 0.2755 -0.0106 0.1294 16.8541 0.0237 0.0035 -0.0027 0.1905 -0.0318 4.3109 0.1654 8.0719 8.0022 8.1331 0.2612 -0.0147 0.1283 16.4589 0.0212 0.0029 -0.0077 0.1840 -0.0336 4.3330 0.1386 7.9354 7.8282 8.1437 0.2386 -0.0212 0.1271 16.0418 0.0176 0.0020 -0.0153 0.1731 -0.0370 4.3551 0.0883 7.7894 7.6411 8.5865 0.1934 -0.0341 0.1260 15.6019 0.0111 0.0008 -0.0303 0.1504 -0.0443 4.3750 0.0083 7.6500 7.6500 7.6500 0.1192 -0.0549 0.1250 15.5516 0.0010 0.0000 -0.0549 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) = 0.056112 TOTAL WEIGHT (Kg) = 0.025448 TOTAL VOLUME (IN**3) = 0.914142 TOTAL PROJECTED AREA (IN**2) = 4.2394 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000278 MOMENT OF INERTIA (Kg-M**2) = 0.000031 STATIC MOMENT, ONE SIDE (IN-LB) = 0.028936 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) = 39019.48 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.