9x6 (9x6.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 2.5992 0.0000 0.0000 0.4000 0.0000 0.4852 0.0000 0.3882 0.0000 0.1700 0.0000 0.0000 0.1200 0.7634 2.9296 0.0127 -0.4349 0.3951 0.0049 0.4555 0.9676 0.3477 0.2570 0.1721 0.0124 -0.0269 0.2400 0.7276 3.2422 0.0989 -0.8401 0.3923 0.0182 0.4272 3.7506 0.3108 0.2488 0.1776 0.0283 -0.0265 0.3600 0.6964 3.5369 0.3214 -1.1067 0.3915 0.0375 0.4002 8.0876 0.2787 0.2357 0.1854 0.0462 -0.0246 0.4800 0.6739 3.8138 0.7284 -1.1287 0.3926 0.0609 0.3746 13.5784 0.2525 0.2184 0.1946 0.0653 -0.0209 0.6000 0.6626 4.0728 1.3446 -0.8331 0.3955 0.0862 0.3504 19.6293 0.2322 0.1988 0.2041 0.0849 -0.0157 0.7200 0.6624 4.3140 2.1593 -0.1937 0.4001 0.1114 0.3276 25.5154 0.2170 0.1786 0.2133 0.1039 -0.0092 0.8400 0.6706 4.5372 3.1137 0.7470 0.4062 0.1345 0.3061 30.5382 0.2053 0.1592 0.2213 0.1218 -0.0017 0.9600 0.6824 4.7427 4.0916 1.8601 0.4137 0.1534 0.2861 34.1500 0.1952 0.1415 0.2270 0.1376 0.0066 1.0800 0.6924 4.9303 4.9219 2.9248 0.4225 0.1661 0.2673 35.9539 0.1851 0.1260 0.2293 0.1508 0.0150 1.2000 0.6965 5.1000 5.3986 3.6491 0.4325 0.1706 0.2500 35.6029 0.1741 0.1133 0.2270 0.1604 0.0229 1.3191 0.6970 5.2507 5.5642 4.0212 0.4432 0.1687 0.2341 33.8762 0.1632 0.1031 0.2212 0.1675 0.0289 1.4219 0.6992 5.3668 5.6885 4.3197 0.4528 0.1662 0.2215 32.4856 0.1549 0.0956 0.2156 0.1735 0.0324 1.5238 0.7026 5.4689 5.7969 4.5940 0.4624 0.1629 0.2100 31.1935 0.1476 0.0892 0.2097 0.1791 0.0344 1.6257 0.7072 5.5581 5.8912 4.8449 0.4719 0.1588 0.1995 29.9741 0.1411 0.0837 0.2032 0.1843 0.0351 1.7276 0.7126 5.6344 5.9718 5.0701 0.4811 0.1539 0.1900 28.8175 0.1354 0.0790 0.1963 0.1891 0.0346 1.8295 0.7186 5.6978 6.0390 5.2679 0.4900 0.1481 0.1815 27.7157 0.1304 0.0749 0.1889 0.1934 0.0330 1.9314 0.7248 5.7484 6.0933 5.4365 0.4983 0.1416 0.1739 26.6622 0.1261 0.0716 0.1811 0.1971 0.0304 2.0333 0.7311 5.7861 6.1352 5.5746 0.5059 0.1343 0.1674 25.6517 0.1224 0.0688 0.1727 0.2002 0.0269 2.1352 0.7371 5.8109 6.1649 5.6812 0.5126 0.1262 0.1618 24.6800 0.1193 0.0665 0.1639 0.2027 0.0225 2.2371 0.7426 5.8237 6.1837 5.7562 0.5183 0.1173 0.1572 23.7463 0.1168 0.0648 0.1546 0.2045 0.0174 2.3390 0.7472 5.8339 6.2014 5.8086 0.5228 0.1077 0.1537 22.8786 0.1148 0.0636 0.1448 0.2056 0.0114 2.4409 0.7508 5.8441 6.2212 5.8407 0.5259 0.0973 0.1511 22.0798 0.1134 0.0629 0.1346 0.2061 0.0046 2.5428 0.7530 5.8543 6.2429 5.8543 0.5275 0.0862 0.1494 21.3431 0.1125 0.0624 0.1240 0.2057 -0.0030 2.6447 0.7536 5.8645 6.2647 5.8645 0.5274 0.0748 0.1478 20.6569 0.1114 0.0619 0.1129 0.2046 -0.0110 2.7466 0.7522 5.8747 6.2861 5.8748 0.5256 0.0631 0.1463 20.0148 0.1100 0.0610 0.1014 0.2025 -0.0192 2.8484 0.7486 5.8848 6.3070 5.8850 0.5217 0.0512 0.1448 19.4125 0.1084 0.0597 0.0895 0.1994 -0.0277 2.9503 0.7425 5.8950 6.3274 5.8952 0.5156 0.0391 0.1432 18.8463 0.1064 0.0582 0.0773 0.1954 -0.0364 3.0522 0.7336 5.9052 6.3472 5.9054 0.5073 0.0268 0.1417 18.3128 0.1040 0.0562 0.0647 0.1902 -0.0452 3.1541 0.7217 5.9154 6.3663 5.9155 0.4964 0.0144 0.1402 17.8090 0.1012 0.0538 0.0517 0.1840 -0.0541 3.2560 0.7064 5.9256 6.3846 5.9257 0.4830 0.0019 0.1387 17.3321 0.0980 0.0510 0.0385 0.1766 -0.0630 3.3579 0.6876 5.9358 6.4020 5.9359 0.4667 -0.0106 0.1371 16.8796 0.0943 0.0478 0.0250 0.1680 -0.0718 3.4598 0.6648 5.9460 6.4183 5.9461 0.4475 -0.0232 0.1356 16.4491 0.0901 0.0442 0.0112 0.1582 -0.0806 3.5617 0.6378 5.9562 6.4334 5.9563 0.4251 -0.0357 0.1341 16.0385 0.0855 0.0402 -0.0027 0.1472 -0.0892 3.6636 0.6064 5.9664 6.4468 5.9664 0.3995 -0.0482 0.1325 15.6456 0.0804 0.0360 -0.0169 0.1348 -0.0976 3.7655 0.5702 5.9766 6.4584 5.9763 0.3705 -0.0605 0.1310 15.2684 0.0747 0.0315 -0.0312 0.1211 -0.1057 3.8674 0.5291 5.9867 6.4826 5.9668 0.3379 -0.0724 0.1295 14.9372 0.0685 0.0268 -0.0456 0.1059 -0.1137 3.9693 0.4828 5.9969 6.5380 5.9380 0.3015 -0.0835 0.1280 14.6895 0.0618 0.0221 -0.0598 0.0894 -0.1214 4.0712 0.4311 5.9893 6.6198 5.8868 0.2612 -0.0938 0.1264 14.5092 0.0545 0.0174 -0.0738 0.0714 -0.1284 4.1731 0.3735 5.9118 6.6865 5.7767 0.2168 -0.1036 0.1249 14.3061 0.0467 0.0130 -0.0874 0.0517 -0.1345 4.2709 0.3125 5.7688 6.7367 5.6268 0.1703 -0.1127 0.1234 14.0925 0.0386 0.0090 -0.1003 0.0315 -0.1396 4.2977 0.2946 5.7178 6.7473 5.5797 0.1568 -0.1153 0.1230 14.0291 0.0363 0.0080 -0.1038 0.0257 -0.1409 4.3205 0.2792 5.6706 6.7546 5.5383 0.1451 -0.1174 0.1227 13.9727 0.0343 0.0071 -0.1068 0.0207 -0.1420 4.3432 0.2634 5.6198 6.7598 5.4955 0.1332 -0.1196 0.1224 13.9128 0.0322 0.0064 -0.1098 0.0156 -0.1430 4.3659 0.2473 5.5653 6.7691 5.4506 0.1211 -0.1218 0.1220 13.8615 0.0302 0.0056 -0.1128 0.0104 -0.1440 4.3886 0.2308 5.5072 6.7684 5.4056 0.1088 -0.1241 0.1217 13.7910 0.0281 0.0049 -0.1159 0.0052 -0.1451 4.4114 0.2115 5.4455 6.7628 5.3599 0.0938 -0.1270 0.1213 13.7117 0.0257 0.0041 -0.1197 -0.0014 -0.1464 4.4341 0.1862 5.3801 6.7505 5.3417 0.0732 -0.1313 0.1210 13.6202 0.0225 0.0032 -0.1250 -0.0111 -0.1486 4.4568 0.1512 5.3111 6.7284 5.4021 0.0432 -0.1378 0.1206 13.5105 0.0182 0.0021 -0.1328 -0.0258 -0.1521 4.4795 0.0896 5.2385 6.6923 5.9170 -0.0125 -0.1504 0.1203 13.3749 0.0108 0.0008 -0.1475 -0.0543 -0.1591 4.5000 0.0072 5.1700 5.1701 5.1699 -0.0888 -0.1681 0.1200 10.3624 0.0009 0.0000 -0.1681 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.050569 TOTAL WEIGHT (Kg) = 0.022934 TOTAL VOLUME (IN**3) = 0.823838 TOTAL PROJECTED AREA (IN**2) = 5.4202 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000392 MOMENT OF INERTIA (Kg-M**2) = 0.000044 STATIC MOMENT, ONE SIDE (IN-LB) = 0.033699 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 = 91.359 INNER LIMIT (NORMALIZED BY RADIUS) = 0.089 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 18611.95 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.