8x6 (8x6.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 0.8960 0.0000 0.0000 0.4000 0.0000 0.4062 0.0000 0.3250 0.0000 0.1750 0.0000 0.0000 0.1160 0.7639 1.4709 0.0118 -0.2738 0.3948 0.0078 0.4046 0.9282 0.3091 0.2113 0.1800 0.0135 0.0134 0.2320 0.7274 2.0114 0.0920 -0.5306 0.3906 0.0288 0.3997 3.6126 0.2907 0.2085 0.1934 0.0284 0.0193 0.3480 0.6947 2.5177 0.3011 -0.6849 0.3875 0.0593 0.3915 7.8419 0.2720 0.2020 0.2126 0.0443 0.0295 0.4640 0.6701 2.9895 0.6875 -0.6411 0.3855 0.0959 0.3800 13.2687 0.2546 0.1912 0.2352 0.0607 0.0429 0.5800 0.6566 3.4271 1.2793 -0.3303 0.3845 0.1354 0.3652 19.3435 0.2398 0.1777 0.2589 0.0765 0.0582 0.6960 0.6550 3.8303 2.0722 0.2789 0.3844 0.1744 0.3472 25.3542 0.2274 0.1630 0.2815 0.0909 0.0739 0.8120 0.6634 4.1991 3.0147 1.1603 0.3854 0.2096 0.3258 30.5786 0.2161 0.1483 0.3007 0.1032 0.0886 0.9280 0.6774 4.5336 3.9975 2.2104 0.3873 0.2376 0.3012 34.4336 0.2040 0.1343 0.3142 0.1125 0.1006 1.0440 0.6922 4.8338 4.8554 3.2434 0.3901 0.2553 0.2742 36.5083 0.1898 0.1214 0.3198 0.1181 0.1085 1.1600 0.7037 5.0997 5.3905 4.0107 0.3937 0.2592 0.2500 36.4864 0.1759 0.1099 0.3150 0.1194 0.1106 1.2745 0.7114 5.3284 5.6303 4.4812 0.3979 0.2532 0.2295 35.1111 0.1633 0.0996 0.3032 0.1183 0.1083 1.3630 0.7158 5.4823 5.7892 4.8103 0.4012 0.2477 0.2161 34.0577 0.1547 0.0924 0.2940 0.1179 0.1062 1.4501 0.7188 5.6141 5.9252 5.1011 0.4045 0.2416 0.2049 33.0372 0.1473 0.0861 0.2850 0.1178 0.1039 1.5371 0.7207 5.7266 6.0421 5.3558 0.4076 0.2348 0.1957 32.0304 0.1410 0.0806 0.2760 0.1180 0.1012 1.6241 0.7213 5.8197 6.1406 5.5713 0.4106 0.2273 0.1885 31.0369 0.1359 0.0760 0.2670 0.1184 0.0983 1.7112 0.7206 5.8936 6.2215 5.7450 0.4132 0.2192 0.1833 30.0563 0.1321 0.0723 0.2579 0.1191 0.0950 1.7982 0.7187 5.9480 6.2856 5.8749 0.4155 0.2104 0.1800 29.0884 0.1294 0.0696 0.2489 0.1201 0.0914 1.8852 0.7155 5.9832 6.3317 5.9595 0.4173 0.2013 0.1779 28.1258 0.1273 0.0675 0.2399 0.1212 0.0876 1.9723 0.7110 5.9990 6.3578 5.9977 0.4187 0.1922 0.1757 27.1601 0.1249 0.0656 0.2309 0.1226 0.0838 2.0593 0.7051 6.0000 6.3685 6.0000 0.4194 0.1831 0.1735 26.2062 0.1224 0.0636 0.2219 0.1242 0.0799 2.1463 0.6980 6.0000 6.3778 6.0001 0.4194 0.1743 0.1713 25.3108 0.1196 0.0616 0.2129 0.1258 0.0761 2.2334 0.6895 6.0000 6.3867 6.0002 0.4186 0.1655 0.1692 24.4716 0.1166 0.0593 0.2039 0.1274 0.0723 2.3204 0.6796 6.0000 6.3950 6.0003 0.4170 0.1569 0.1670 23.6837 0.1135 0.0568 0.1949 0.1288 0.0684 2.4074 0.6683 6.0000 6.4029 6.0003 0.4144 0.1484 0.1648 22.9424 0.1101 0.0543 0.1859 0.1300 0.0645 2.4945 0.6556 6.0000 6.4101 6.0003 0.4108 0.1401 0.1626 22.2437 0.1066 0.0515 0.1770 0.1309 0.0607 2.5815 0.6414 6.0000 6.4168 6.0003 0.4060 0.1319 0.1605 21.5840 0.1029 0.0487 0.1680 0.1314 0.0568 2.6686 0.6258 6.0000 6.4227 6.0002 0.4001 0.1238 0.1583 20.9598 0.0991 0.0457 0.1590 0.1315 0.0530 2.7556 0.6087 6.0000 6.4280 6.0002 0.3929 0.1159 0.1561 20.3681 0.0950 0.0427 0.1500 0.1309 0.0492 2.8426 0.5900 6.0000 6.4325 6.0002 0.3843 0.1080 0.1539 19.8063 0.0908 0.0396 0.1410 0.1298 0.0454 2.9297 0.5698 6.0000 6.4361 6.0002 0.3743 0.1003 0.1518 19.2718 0.0865 0.0364 0.1320 0.1279 0.0416 3.0167 0.5481 6.0000 6.4387 6.0002 0.3627 0.0927 0.1496 18.7624 0.0820 0.0332 0.1231 0.1252 0.0378 3.1037 0.5248 6.0000 6.4402 6.0002 0.3496 0.0852 0.1474 18.2757 0.0774 0.0300 0.1141 0.1216 0.0341 3.1908 0.4999 6.0000 6.4405 6.0002 0.3347 0.0777 0.1452 17.8097 0.0726 0.0269 0.1051 0.1171 0.0304 3.2778 0.4733 5.9915 6.4308 5.9916 0.3180 0.0704 0.1431 17.3409 0.0677 0.0238 0.0961 0.1115 0.0269 3.3648 0.4451 5.9618 6.3980 5.9619 0.2995 0.0631 0.1409 16.8371 0.0627 0.0207 0.0871 0.1047 0.0234 3.4519 0.4153 5.9108 6.3418 5.9109 0.2791 0.0558 0.1387 16.2990 0.0576 0.0178 0.0782 0.0968 0.0201 3.5389 0.3837 5.8385 6.2616 5.8386 0.2565 0.0486 0.1365 15.7274 0.0524 0.0150 0.0692 0.0876 0.0168 3.6259 0.3504 5.7449 6.1566 5.7450 0.2319 0.0414 0.1344 15.1221 0.0471 0.0123 0.0602 0.0770 0.0136 3.7130 0.3154 5.6300 6.0256 5.6301 0.2051 0.0343 0.1322 14.4822 0.0417 0.0099 0.0512 0.0650 0.0104 3.7965 0.2801 5.4997 5.8736 5.4998 0.1772 0.0275 0.1301 13.8327 0.0364 0.0077 0.0426 0.0522 0.0074 3.8202 0.2698 5.4592 5.8254 5.4592 0.1689 0.0256 0.1295 13.6417 0.0349 0.0071 0.0401 0.0483 0.0065 3.8404 0.2609 5.4234 5.7825 5.4234 0.1617 0.0240 0.1290 13.4761 0.0337 0.0066 0.0381 0.0448 0.0057 3.8606 0.2518 5.3864 5.7377 5.3865 0.1542 0.0224 0.1285 13.3082 0.0323 0.0062 0.0359 0.0412 0.0050 3.8808 0.2404 5.3483 5.6915 5.3488 0.1445 0.0203 0.1280 13.1383 0.0308 0.0056 0.0332 0.0364 0.0039 3.9010 0.2258 5.3091 5.6436 5.3105 0.1316 0.0175 0.1275 12.9663 0.0288 0.0049 0.0296 0.0299 0.0022 3.9212 0.2070 5.2687 5.5938 5.2869 0.1145 0.0138 0.1270 12.7917 0.0263 0.0041 0.0249 0.0211 0.0000 3.9414 0.1822 5.2271 5.5420 5.2794 0.0916 0.0089 0.1265 12.6142 0.0230 0.0032 0.0187 0.0090 -0.0031 3.9616 0.1464 5.1844 5.4880 5.3172 0.0579 0.0018 0.1260 12.4334 0.0184 0.0021 0.0097 -0.0090 -0.0079 3.9818 0.0798 5.1406 5.4329 5.6592 -0.0061 -0.0117 0.1255 12.2520 0.0100 0.0006 -0.0074 -0.0434 -0.0171 4.0000 0.0093 5.1002 5.1002 5.1002 -0.0740 -0.0259 0.1250 11.4712 0.0012 0.0000 -0.0259 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) = 0.041064 TOTAL WEIGHT (Kg) = 0.018623 TOTAL VOLUME (IN**3) = 0.668979 TOTAL PROJECTED AREA (IN**2) = 4.4279 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000235 MOMENT OF INERTIA (Kg-M**2) = 0.000026 STATIC MOMENT, ONE SIDE (IN-LB) = 0.023865 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 = 88.487 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 35551.12 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.