7x3 (7x3.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 2.3180 0.0000 0.0000 0.3250 0.0000 0.4308 0.0000 0.2800 0.0000 0.0900 0.0000 0.0000 0.0800 0.6257 2.3306 0.0073 -0.2917 0.3221 0.0013 0.4296 0.8363 0.2688 0.1484 0.0916 0.0074 -0.0457 0.1600 0.6020 2.3432 0.0563 -0.5596 0.3213 0.0048 0.4261 3.2067 0.2565 0.1476 0.0959 0.0190 -0.0477 0.2400 0.5815 2.3557 0.1809 -0.7395 0.3222 0.0099 0.4203 6.8396 0.2444 0.1452 0.1021 0.0323 -0.0495 0.3200 0.5666 2.3683 0.4040 -0.7665 0.3246 0.0160 0.4122 11.3613 0.2335 0.1401 0.1093 0.0465 -0.0506 0.4000 0.5588 2.3809 0.7338 -0.6023 0.3284 0.0226 0.4017 16.2763 0.2245 0.1333 0.1167 0.0608 -0.0507 0.4800 0.5582 2.3935 1.1580 -0.2408 0.3331 0.0292 0.3889 21.0057 0.2171 0.1255 0.1236 0.0744 -0.0497 0.5600 0.5633 2.4060 1.6394 0.2821 0.3387 0.0352 0.3738 24.9823 0.2106 0.1172 0.1290 0.0867 -0.0475 0.6400 0.5715 2.4186 2.1136 0.8823 0.3447 0.0401 0.3564 27.7273 0.2036 0.1090 0.1322 0.0970 -0.0442 0.7200 0.5799 2.4312 2.4932 1.4290 0.3511 0.0433 0.3366 28.8597 0.1952 0.1010 0.1325 0.1046 -0.0397 0.8000 0.5866 2.4438 2.6779 1.7591 0.3575 0.0444 0.3145 28.0468 0.1845 0.0933 0.1291 0.1091 -0.0344 0.8802 0.5919 2.4564 2.7018 1.8821 0.3641 0.0442 0.2909 26.0365 0.1722 0.0860 0.1233 0.1119 -0.0290 0.9643 0.5973 2.4696 2.7212 1.9990 0.3717 0.0438 0.2677 24.1861 0.1599 0.0788 0.1170 0.1159 -0.0244 1.0486 0.6025 2.4828 2.7372 2.1061 0.3797 0.0431 0.2462 22.5602 0.1483 0.0723 0.1105 0.1205 -0.0209 1.1329 0.6074 2.4961 2.7504 2.2029 0.3880 0.0419 0.2264 21.1256 0.1376 0.0664 0.1038 0.1258 -0.0186 1.2172 0.6120 2.5094 2.7614 2.2896 0.3964 0.0402 0.2084 19.8526 0.1276 0.0610 0.0970 0.1314 -0.0173 1.3016 0.6161 2.5226 2.7709 2.3660 0.4048 0.0380 0.1922 18.7181 0.1184 0.0561 0.0900 0.1373 -0.0170 1.3859 0.6195 2.5359 2.7796 2.4320 0.4130 0.0351 0.1777 17.7037 0.1101 0.0518 0.0828 0.1433 -0.0176 1.4702 0.6223 2.5491 2.7879 2.4874 0.4208 0.0315 0.1649 16.7944 0.1026 0.0480 0.0755 0.1493 -0.0191 1.5545 0.6242 2.5624 2.7967 2.5321 0.4282 0.0273 0.1539 15.9783 0.0961 0.0447 0.0679 0.1552 -0.0215 1.6388 0.6252 2.5756 2.8063 2.5658 0.4348 0.0223 0.1447 15.2453 0.0905 0.0419 0.0602 0.1609 -0.0247 1.7231 0.6251 2.5889 2.8176 2.5883 0.4406 0.0165 0.1372 14.5874 0.0858 0.0397 0.0523 0.1663 -0.0287 1.8074 0.6238 2.6021 2.8309 2.6021 0.4454 0.0101 0.1315 13.9975 0.0820 0.0379 0.0443 0.1713 -0.0334 1.8917 0.6212 2.6154 2.8469 2.6154 0.4490 0.0028 0.1275 13.4697 0.0792 0.0364 0.0360 0.1757 -0.0387 1.9760 0.6171 2.6286 2.8662 2.6287 0.4513 -0.0052 0.1253 12.9991 0.0773 0.0353 0.0276 0.1795 -0.0447 2.0603 0.6114 2.6419 2.8881 2.6419 0.4521 -0.0138 0.1244 12.5765 0.0761 0.0344 0.0190 0.1826 -0.0511 2.1447 0.6041 2.6551 2.9099 2.6552 0.4513 -0.0224 0.1236 12.1855 0.0746 0.0334 0.0103 0.1848 -0.0576 2.2290 0.5949 2.6684 2.9314 2.6684 0.4486 -0.0311 0.1227 11.8218 0.0730 0.0321 0.0013 0.1860 -0.0642 2.3133 0.5837 2.6816 2.9525 2.6817 0.4439 -0.0398 0.1219 11.4823 0.0711 0.0307 -0.0078 0.1860 -0.0710 2.3976 0.5704 2.6949 2.9731 2.6949 0.4371 -0.0486 0.1210 11.1644 0.0690 0.0292 -0.0171 0.1849 -0.0778 2.4819 0.5550 2.7082 2.9933 2.7082 0.4280 -0.0573 0.1202 10.8657 0.0667 0.0274 -0.0266 0.1824 -0.0846 2.5662 0.5372 2.7214 3.0129 2.7214 0.4164 -0.0661 0.1193 10.5841 0.0641 0.0255 -0.0362 0.1785 -0.0915 2.6505 0.5169 2.7347 3.0318 2.7347 0.4021 -0.0749 0.1185 10.3176 0.0612 0.0235 -0.0460 0.1731 -0.0985 2.7348 0.4940 2.7479 3.0498 2.7480 0.3851 -0.0837 0.1177 10.0644 0.0581 0.0213 -0.0561 0.1659 -0.1054 2.8191 0.4684 2.7559 3.0615 2.7560 0.3651 -0.0925 0.1168 9.8061 0.0547 0.0190 -0.0662 0.1570 -0.1124 2.9034 0.4400 2.7485 3.0565 2.7486 0.3420 -0.1013 0.1160 9.5113 0.0510 0.0167 -0.0766 0.1463 -0.1192 2.9878 0.4085 2.7256 3.0341 2.7256 0.3156 -0.1103 0.1151 9.1810 0.0470 0.0143 -0.0871 0.1335 -0.1260 3.0721 0.3740 2.6869 2.9960 2.6870 0.2857 -0.1192 0.1143 8.8227 0.0427 0.0119 -0.0978 0.1187 -0.1327 3.1564 0.3363 2.6327 2.9468 2.6327 0.2522 -0.1281 0.1134 8.4515 0.0381 0.0096 -0.1087 0.1020 -0.1394 3.2407 0.2951 2.5628 2.8887 2.5628 0.2150 -0.1370 0.1126 8.0745 0.0332 0.0073 -0.1198 0.0832 -0.1461 3.3215 0.2524 2.4812 2.8285 2.4812 0.1756 -0.1455 0.1118 7.7184 0.0282 0.0053 -0.1305 0.0632 -0.1525 3.3427 0.2407 2.4574 2.8129 2.4574 0.1647 -0.1477 0.1116 7.6283 0.0269 0.0048 -0.1334 0.0577 -0.1541 3.3604 0.2308 2.4368 2.8001 2.4368 0.1553 -0.1495 0.1114 7.5546 0.0257 0.0044 -0.1358 0.0529 -0.1555 3.3780 0.2206 2.4156 2.7878 2.4156 0.1458 -0.1513 0.1112 7.4827 0.0245 0.0040 -0.1382 0.0481 -0.1569 3.3957 0.2098 2.3936 2.7762 2.3937 0.1356 -0.1532 0.1110 7.4135 0.0233 0.0036 -0.1407 0.0428 -0.1584 3.4134 0.1963 2.3709 2.7659 2.3719 0.1227 -0.1554 0.1109 7.3486 0.0218 0.0031 -0.1436 0.0361 -0.1601 3.4311 0.1792 2.3476 2.7573 2.3518 0.1062 -0.1581 0.1107 7.2885 0.0198 0.0026 -0.1473 0.0273 -0.1622 3.4487 0.1569 2.3236 2.7506 2.3330 0.0845 -0.1613 0.1105 7.2343 0.0173 0.0020 -0.1518 0.0156 -0.1648 3.4664 0.1250 2.2989 2.7467 2.3160 0.0532 -0.1657 0.1103 7.1877 0.0138 0.0013 -0.1581 -0.0015 -0.1684 3.4841 0.0675 2.2735 2.7484 2.3015 -0.0035 -0.1732 0.1102 7.1560 0.0074 0.0004 -0.1691 -0.0329 -0.1746 3.5000 0.0073 2.2500 2.2501 2.2500 -0.0628 -0.1811 0.1100 5.8420 0.0008 0.0000 -0.1811 0.0000 0.0000 RADIUS: 3.50 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.024427 TOTAL WEIGHT (Kg) = 0.011078 TOTAL VOLUME (IN**3) = 0.397950 TOTAL PROJECTED AREA (IN**2) = 3.6019 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000106 MOMENT OF INERTIA (Kg-M**2) = 0.000012 STATIC MOMENT, ONE SIDE (IN-LB) = 0.012239 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) = 33875.42 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.