7x8 (7x8.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 0.6500 2.8953 0.0000 0.0000 0.3250 0.0000 0.3255 0.0000 0.2116 0.0000 0.0600 0.0000 0.0000 0.0900 0.6189 3.4370 0.0120 -0.4752 0.3218 0.0058 0.3159 1.2169 0.1955 0.1718 0.0650 0.0090 -0.0922 0.1800 0.5829 3.9483 0.0949 -0.9322 0.3210 0.0215 0.3065 4.7970 0.1787 0.1666 0.0786 0.0272 -0.0861 0.2700 0.5483 4.4293 0.3181 -1.2662 0.3222 0.0443 0.2975 10.6191 0.1631 0.1578 0.0981 0.0490 -0.0755 0.3600 0.5224 4.8798 0.7498 -1.3566 0.3253 0.0717 0.2887 18.3395 0.1508 0.1458 0.1215 0.0729 -0.0616 0.4500 0.5106 5.3000 1.4504 -1.0897 0.3299 0.1012 0.2802 27.1565 0.1431 0.1322 0.1468 0.0976 -0.0461 0.5400 0.5145 5.6898 2.4523 -0.3772 0.3357 0.1303 0.2720 35.8584 0.1400 0.1184 0.1720 0.1214 -0.0306 0.6300 0.5310 6.0493 3.7236 0.7965 0.3425 0.1564 0.2641 43.2493 0.1402 0.1058 0.1948 0.1430 -0.0164 0.7200 0.5531 6.3783 5.1210 2.3035 0.3500 0.1772 0.2565 48.5429 0.1419 0.0952 0.2129 0.1606 -0.0049 0.8100 0.5735 6.6770 6.3658 3.8169 0.3578 0.1902 0.2492 51.3580 0.1429 0.0874 0.2239 0.1727 0.0030 0.9000 0.5862 6.9453 7.0961 4.8487 0.3659 0.1928 0.2421 51.4487 0.1419 0.0826 0.2253 0.1779 0.0063 0.9895 0.5926 7.1820 7.3611 5.3580 0.3740 0.1879 0.2355 49.8153 0.1395 0.0795 0.2199 0.1789 0.0064 1.0705 0.5981 7.3704 7.5699 5.7874 0.3818 0.1830 0.2296 48.3770 0.1373 0.0767 0.2144 0.1804 0.0059 1.1510 0.6032 7.5332 7.7515 6.1840 0.3898 0.1776 0.2241 46.9852 0.1352 0.0739 0.2086 0.1823 0.0049 1.2316 0.6080 7.6717 7.9076 6.5464 0.3978 0.1717 0.2188 45.6208 0.1330 0.0713 0.2023 0.1846 0.0034 1.3121 0.6123 7.7859 8.0381 6.8710 0.4058 0.1653 0.2137 44.2754 0.1309 0.0686 0.1956 0.1871 0.0016 1.3926 0.6160 7.8758 8.1430 7.1545 0.4136 0.1585 0.2089 42.9427 0.1287 0.0661 0.1885 0.1897 -0.0007 1.4731 0.6190 7.9413 8.2226 7.3943 0.4211 0.1512 0.2043 41.6171 0.1265 0.0637 0.1809 0.1924 -0.0032 1.5536 0.6213 7.9826 8.2768 7.5881 0.4281 0.1434 0.1999 40.2943 0.1242 0.0614 0.1729 0.1950 -0.0062 1.6341 0.6226 7.9995 8.3058 7.7341 0.4345 0.1351 0.1958 38.9707 0.1219 0.0592 0.1645 0.1974 -0.0094 1.7147 0.6229 8.0000 8.3176 7.8386 0.4401 0.1263 0.1919 37.6698 0.1195 0.0571 0.1556 0.1998 -0.0129 1.7952 0.6221 8.0000 8.3285 7.9169 0.4448 0.1172 0.1882 36.4413 0.1171 0.0551 0.1463 0.2020 -0.0170 1.8757 0.6200 8.0000 8.3389 7.9694 0.4485 0.1076 0.1848 35.2820 0.1146 0.0533 0.1365 0.2040 -0.0216 1.9562 0.6166 8.0000 8.3491 7.9963 0.4509 0.0976 0.1816 34.1871 0.1120 0.0515 0.1263 0.2057 -0.0267 2.0367 0.6118 8.0000 8.3590 8.0000 0.4521 0.0872 0.1786 33.1523 0.1093 0.0498 0.1157 0.2069 -0.0322 2.1172 0.6054 8.0000 8.3682 8.0003 0.4517 0.0765 0.1757 32.1717 0.1064 0.0479 0.1046 0.2075 -0.0381 2.1978 0.5974 8.0000 8.3765 8.0006 0.4498 0.0654 0.1727 31.2411 0.1032 0.0457 0.0930 0.2074 -0.0443 2.2783 0.5876 8.0000 8.3840 8.0007 0.4461 0.0541 0.1698 30.3568 0.0998 0.0435 0.0811 0.2063 -0.0508 2.3588 0.5760 8.0000 8.3905 8.0006 0.4405 0.0423 0.1668 29.5155 0.0961 0.0410 0.0687 0.2042 -0.0575 2.4393 0.5623 8.0000 8.3959 8.0006 0.4329 0.0303 0.1639 28.7140 0.0921 0.0384 0.0558 0.2011 -0.0645 2.5198 0.5466 8.0000 8.4003 8.0005 0.4231 0.0179 0.1609 27.9493 0.0880 0.0356 0.0426 0.1967 -0.0718 2.6003 0.5287 8.0000 8.4035 8.0005 0.4109 0.0052 0.1579 27.2186 0.0835 0.0327 0.0288 0.1911 -0.0793 2.6809 0.5085 8.0000 8.4053 8.0004 0.3963 -0.0078 0.1550 26.5192 0.0788 0.0297 0.0146 0.1840 -0.0871 2.7614 0.4858 7.9997 8.4053 8.0001 0.3791 -0.0212 0.1520 25.8477 0.0739 0.0266 0.0000 0.1755 -0.0951 2.8419 0.4607 7.9820 8.3858 7.9823 0.3592 -0.0349 0.1491 25.1562 0.0687 0.0235 -0.0151 0.1652 -0.1032 2.9224 0.4329 7.9366 8.3363 7.9368 0.3363 -0.0490 0.1461 24.4179 0.0633 0.0204 -0.0306 0.1533 -0.1114 3.0029 0.4023 7.8635 8.2563 7.8637 0.3105 -0.0636 0.1432 23.6333 0.0576 0.0173 -0.0465 0.1394 -0.1197 3.0834 0.3689 7.7628 8.1449 7.7630 0.2814 -0.0784 0.1402 22.8023 0.0517 0.0143 -0.0629 0.1237 -0.1282 3.1640 0.3325 7.6345 8.0010 7.6346 0.2490 -0.0937 0.1373 21.9233 0.0456 0.0114 -0.0798 0.1059 -0.1369 3.2445 0.2931 7.4785 7.8224 7.4785 0.2132 -0.1093 0.1343 20.9927 0.0394 0.0087 -0.0971 0.0861 -0.1459 3.3217 0.2522 7.3028 7.6148 7.3029 0.1755 -0.1246 0.1315 20.0444 0.0332 0.0063 -0.1141 0.0651 -0.1548 3.3427 0.2406 7.2508 7.5515 7.2508 0.1647 -0.1288 0.1307 19.7761 0.0315 0.0057 -0.1188 0.0591 -0.1573 3.3604 0.2307 7.2054 7.4956 7.2054 0.1553 -0.1324 0.1301 19.5455 0.0300 0.0053 -0.1228 0.0539 -0.1594 3.3780 0.2205 7.1587 7.4372 7.1587 0.1458 -0.1359 0.1294 19.3106 0.0285 0.0048 -0.1268 0.0485 -0.1616 3.3957 0.2100 7.1107 7.3761 7.1107 0.1359 -0.1396 0.1288 19.0711 0.0270 0.0043 -0.1309 0.0430 -0.1638 3.4134 0.1971 7.0613 7.3124 7.0617 0.1236 -0.1440 0.1281 18.8270 0.0253 0.0038 -0.1359 0.0362 -0.1665 3.4311 0.1804 7.0106 7.2457 7.0116 0.1078 -0.1496 0.1275 18.5777 0.0230 0.0032 -0.1421 0.0275 -0.1699 3.4487 0.1584 6.9586 7.1755 6.9880 0.0869 -0.1567 0.1268 18.3218 0.0201 0.0025 -0.1501 0.0160 -0.1744 3.4664 0.1270 6.9052 7.1013 7.0122 0.0570 -0.1666 0.1262 18.0583 0.0160 0.0016 -0.1613 -0.0004 -0.1808 3.4841 0.0694 6.8505 7.0230 7.3489 0.0020 -0.1843 0.1255 17.7871 0.0087 0.0005 -0.1814 -0.0303 -0.1922 3.5000 0.0073 6.8002 6.8002 6.8002 -0.0574 -0.2030 0.1250 17.1829 0.0009 0.0000 -0.2030 0.0000 0.0000 RADIUS: 3.50 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.90 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.028082 TOTAL WEIGHT (Kg) = 0.012736 TOTAL VOLUME (IN**3) = 0.457493 TOTAL PROJECTED AREA (IN**2) = 3.0397 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000136 MOMENT OF INERTIA (Kg-M**2) = 0.000015 STATIC MOMENT, ONE SIDE (IN-LB) = 0.015114 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 = 92.969 INNER LIMIT (NORMALIZED BY RADIUS) = 0.093 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 39862.52 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.