8x10 (8x10.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 0.8000 -3.3200 0.0000 0.0000 0.4000 0.0000 0.4062 0.0000 0.3250 0.0000 0.0500 0.0000 0.0000 0.1160 0.7614 -1.8197 -0.0064 -0.5247 0.3955 0.0055 0.4041 -0.5036 0.3077 0.2097 0.0555 0.0103 -0.0991 0.2320 0.7181 -0.4090 0.0628 -1.0285 0.3936 0.0203 0.3976 2.4675 0.2855 0.2057 0.0705 0.0312 -0.0932 0.3480 0.6756 0.9121 0.2805 -1.3956 0.3941 0.0420 0.3868 7.3108 0.2613 0.1972 0.0923 0.0563 -0.0826 0.4640 0.6402 2.1435 0.7166 -1.4887 0.3967 0.0683 0.3716 13.8100 0.2379 0.1836 0.1185 0.0842 -0.0682 0.5800 0.6169 3.2854 1.4323 -1.1850 0.4013 0.0971 0.3521 21.4559 0.2172 0.1670 0.1470 0.1135 -0.0513 0.6960 0.6081 4.3376 2.4641 -0.3895 0.4077 0.1260 0.3289 29.4003 0.2000 0.1491 0.1753 0.1428 -0.0335 0.8120 0.6118 5.3002 3.7960 0.9246 0.4158 0.1529 0.3065 36.6501 0.1875 0.1316 0.2010 0.1707 -0.0163 0.9280 0.6228 6.1732 5.3186 2.6538 0.4252 0.1755 0.2859 42.3696 0.1780 0.1156 0.2218 0.1959 -0.0010 1.0440 0.6340 6.9566 6.7954 4.5007 0.4359 0.1916 0.2670 46.0113 0.1693 0.1019 0.2352 0.2170 0.0110 1.1600 0.6389 7.6504 7.8703 5.9624 0.4476 0.1990 0.2500 47.1979 0.1597 0.0909 0.2388 0.2327 0.0182 1.2745 0.6392 8.2472 8.4888 6.8929 0.4598 0.1998 0.2349 46.6701 0.1502 0.0822 0.2356 0.2439 0.0212 1.3630 0.6412 8.6489 8.9040 7.5535 0.4693 0.1994 0.2245 46.1143 0.1440 0.0767 0.2327 0.2514 0.0225 1.4501 0.6445 8.9929 9.2606 8.1434 0.4785 0.1984 0.2152 45.4664 0.1387 0.0722 0.2297 0.2579 0.0231 1.5371 0.6487 9.2865 9.5663 8.6645 0.4875 0.1968 0.2070 44.7268 0.1343 0.0684 0.2264 0.2635 0.0229 1.6241 0.6537 9.5296 9.8211 9.1084 0.4960 0.1945 0.1997 43.9023 0.1306 0.0654 0.2229 0.2681 0.0223 1.7112 0.6591 9.7222 10.0252 9.4683 0.5040 0.1916 0.1935 42.9975 0.1275 0.0630 0.2190 0.2718 0.0212 1.7982 0.6648 9.8644 10.1788 9.7385 0.5114 0.1881 0.1883 42.0158 0.1251 0.0613 0.2148 0.2745 0.0197 1.8852 0.6704 9.9561 10.2823 9.9151 0.5179 0.1839 0.1840 40.9595 0.1234 0.0602 0.2103 0.2763 0.0179 1.9723 0.6757 9.9974 10.3358 9.9951 0.5234 0.1790 0.1808 39.8301 0.1222 0.0597 0.2054 0.2771 0.0159 2.0593 0.6805 10.0000 10.3510 10.0001 0.5279 0.1734 0.1784 38.6593 0.1214 0.0596 0.2001 0.2769 0.0136 2.1463 0.6845 10.0000 10.3631 10.0004 0.5311 0.1675 0.1760 37.5400 0.1205 0.0595 0.1943 0.2757 0.0108 2.2334 0.6874 10.0000 10.3744 10.0008 0.5329 0.1612 0.1736 36.4754 0.1193 0.0593 0.1881 0.2735 0.0077 2.3204 0.6890 10.0000 10.3849 10.0010 0.5333 0.1545 0.1712 35.4619 0.1179 0.0589 0.1815 0.2702 0.0043 2.4074 0.6890 10.0000 10.3946 10.0010 0.5319 0.1474 0.1688 34.4962 0.1163 0.0584 0.1744 0.2659 0.0007 2.4945 0.6872 10.0000 10.4036 10.0009 0.5287 0.1399 0.1664 33.5753 0.1144 0.0575 0.1668 0.2606 -0.0031 2.5815 0.6834 10.0000 10.4116 10.0009 0.5236 0.1320 0.1640 32.6961 0.1121 0.0564 0.1587 0.2544 -0.0071 2.6686 0.6771 10.0000 10.4187 10.0008 0.5164 0.1237 0.1616 31.8559 0.1094 0.0548 0.1500 0.2472 -0.0111 2.7556 0.6683 10.0000 10.4243 10.0008 0.5070 0.1149 0.1592 31.0514 0.1064 0.0528 0.1407 0.2391 -0.0152 2.8426 0.6566 10.0000 10.4288 10.0007 0.4952 0.1057 0.1568 30.2804 0.1030 0.0503 0.1309 0.2301 -0.0194 2.9297 0.6418 10.0000 10.4320 10.0007 0.4809 0.0960 0.1544 29.5413 0.0991 0.0474 0.1204 0.2202 -0.0237 3.0167 0.6236 10.0000 10.4341 10.0006 0.4640 0.0858 0.1520 28.8321 0.0948 0.0441 0.1093 0.2093 -0.0281 3.1037 0.6017 10.0000 10.4345 10.0005 0.4442 0.0750 0.1496 28.1498 0.0900 0.0404 0.0976 0.1973 -0.0325 3.1908 0.5760 10.0000 10.4327 10.0005 0.4216 0.0637 0.1473 27.4916 0.0848 0.0365 0.0851 0.1841 -0.0372 3.2778 0.5461 9.9858 10.4139 9.9862 0.3958 0.0518 0.1449 26.8235 0.0791 0.0323 0.0720 0.1695 -0.0418 3.3648 0.5117 9.9363 10.3561 9.9366 0.3668 0.0393 0.1425 26.0975 0.0729 0.0279 0.0581 0.1536 -0.0464 3.4519 0.4727 9.8513 10.2582 9.8516 0.3345 0.0262 0.1401 25.3129 0.0662 0.0235 0.0434 0.1362 -0.0510 3.5389 0.4287 9.7308 10.1183 9.7310 0.2987 0.0125 0.1377 24.4680 0.0590 0.0191 0.0280 0.1175 -0.0557 3.6259 0.3796 9.5748 9.9337 9.5749 0.2593 -0.0019 0.1353 23.5583 0.0514 0.0148 0.0118 0.0974 -0.0605 3.7130 0.3249 9.3832 9.6986 9.3833 0.2160 -0.0170 0.1329 22.5740 0.0432 0.0107 -0.0052 0.0760 -0.0656 3.7965 0.2671 9.1659 9.4147 9.1660 0.1709 -0.0321 0.1306 21.5380 0.0349 0.0072 -0.0224 0.0542 -0.0708 3.8202 0.2497 9.0984 9.3210 9.0984 0.1574 -0.0364 0.1299 21.2225 0.0325 0.0063 -0.0274 0.0477 -0.0724 3.8404 0.2346 9.0387 9.2353 9.0387 0.1456 -0.0402 0.1294 20.9433 0.0303 0.0055 -0.0317 0.0422 -0.0737 3.8606 0.2191 8.9771 9.1433 8.9771 0.1337 -0.0440 0.1288 20.6532 0.0282 0.0048 -0.0360 0.0366 -0.0751 3.8808 0.2032 8.9136 9.0440 8.9136 0.1215 -0.0479 0.1283 20.3499 0.0261 0.0042 -0.0405 0.0309 -0.0765 3.9010 0.1870 8.8481 8.9359 8.8481 0.1091 -0.0517 0.1277 20.0303 0.0239 0.0035 -0.0449 0.0252 -0.0779 3.9212 0.1705 8.7808 8.8166 8.7808 0.0964 -0.0556 0.1272 19.6898 0.0217 0.0030 -0.0494 0.0194 -0.0794 3.9414 0.1513 8.7115 8.6830 8.7115 0.0813 -0.0604 0.1266 19.3216 0.0192 0.0023 -0.0549 0.0124 -0.0814 3.9616 0.1242 8.6403 8.5295 8.6824 0.0590 -0.0678 0.1261 18.9149 0.0157 0.0016 -0.0633 0.0016 -0.0850 3.9818 0.0791 8.5673 8.3474 8.9798 0.0197 -0.0811 0.1255 18.4513 0.0099 0.0007 -0.0782 -0.0179 -0.0923 4.0000 0.0052 8.4998 8.4999 8.4998 -0.0472 -0.1037 0.1250 18.6855 0.0006 0.0000 -0.1037 0.0000 0.0000 RADIUS: 4.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.16 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.039501 TOTAL WEIGHT (Kg) = 0.017914 TOTAL VOLUME (IN**3) = 0.643516 TOTAL PROJECTED AREA (IN**2) = 3.9800 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000253 MOMENT OF INERTIA (Kg-M**2) = 0.000029 STATIC MOMENT, ONE SIDE (IN-LB) = 0.024130 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 = 92.759 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 22338.86 BASED ON MODULUS (MILLION) = 1.60 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.