FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 74-Cl5-140 MOD (smoothed) (fx74modsm-il) Reynolds number: 100,000 Max Cl/Cd: 58.14 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74modsm-il-100000-n5.txt Download as CSV file: xf-fx74modsm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-Cl5-140 MOD (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 0.2177 0.10185 0.09606 -0.1192 0.7572 0.0296
-8.750 0.2291 0.09958 0.09371 -0.1208 0.7470 0.0305
-8.500 0.2389 0.09763 0.09173 -0.1223 0.7367 0.0313
-8.250 0.2479 0.09610 0.09016 -0.1242 0.7278 0.0318
-8.000 0.2551 0.09492 0.08894 -0.1262 0.7189 0.0321
-7.750 0.2617 0.09373 0.08774 -0.1281 0.7107 0.0323
-7.500 0.2687 0.09234 0.08633 -0.1300 0.7029 0.0324
-7.250 0.2825 0.08839 0.08234 -0.1297 0.6961 0.0327
-7.000 0.2974 0.08467 0.07857 -0.1290 0.6891 0.0335
-6.750 0.3090 0.08230 0.07613 -0.1294 0.6831 0.0343
-6.500 0.3185 0.08029 0.07413 -0.1298 0.6760 0.0352
-6.250 0.3280 0.07838 0.07218 -0.1305 0.6702 0.0362
-6.000 0.3359 0.07671 0.07051 -0.1310 0.6643 0.0372
-5.750 0.3463 0.07501 0.06881 -0.1326 0.6583 0.0388
-5.500 0.3634 0.07405 0.06780 -0.1391 0.6534 0.0406
-5.250 0.3907 0.07258 0.06633 -0.1495 0.6474 0.0412
-5.000 0.3894 0.06879 0.06256 -0.1417 0.6424 0.0424
-4.750 0.4028 0.06646 0.06017 -0.1413 0.6379 0.0441
-4.500 0.4189 0.06438 0.05808 -0.1433 0.6327 0.0458
-4.250 0.4388 0.06219 0.05588 -0.1468 0.6275 0.0481
-4.000 0.4992 0.05927 0.05276 -0.1664 0.6227 0.0521
-3.750 0.5245 0.05575 0.04920 -0.1709 0.6184 0.0530
-3.500 0.5302 0.05367 0.04718 -0.1672 0.6135 0.0544
-3.250 0.5508 0.05154 0.04499 -0.1684 0.6090 0.0568
-3.000 0.6082 0.04815 0.04133 -0.1815 0.6050 0.0643
-2.750 0.6414 0.04511 0.03828 -0.1870 0.5999 0.0691
-2.500 0.6996 0.04184 0.03474 -0.1988 0.5951 0.0830
-2.250 0.7259 0.03993 0.03277 -0.2002 0.5913 0.0874
-2.000 0.7787 0.03719 0.02977 -0.2090 0.5870 0.1018
-1.500 0.9242 0.02901 0.02011 -0.2309 0.5778 0.0435
-1.250 0.9720 0.02759 0.01796 -0.2351 0.5744 0.0416
-1.000 1.0076 0.02671 0.01677 -0.2371 0.5700 0.0414
-0.750 1.0418 0.02583 0.01565 -0.2388 0.5655 0.0417
-0.500 1.0744 0.02518 0.01486 -0.2403 0.5616 0.0447
-0.250 1.1070 0.02475 0.01418 -0.2413 0.5584 0.0474
0.000 1.1352 0.02447 0.01383 -0.2415 0.5542 0.0486
0.250 1.1634 0.02428 0.01357 -0.2418 0.5501 0.0504
0.500 1.1934 0.02408 0.01330 -0.2424 0.5464 0.0544
0.750 1.2252 0.02398 0.01308 -0.2434 0.5433 0.0612
1.000 1.2541 0.02406 0.01307 -0.2439 0.5394 0.0682
1.250 1.2826 0.02416 0.01317 -0.2444 0.5352 0.0885
1.500 1.3136 0.02337 0.01380 -0.2455 0.5318 0.7109
1.750 1.3270 0.02312 0.01366 -0.2422 0.5289 1.0000
2.000 1.3553 0.02346 0.01376 -0.2425 0.5259 1.0000
2.250 1.3784 0.02396 0.01420 -0.2420 0.5215 1.0000
2.500 1.4035 0.02439 0.01451 -0.2418 0.5178 1.0000
2.750 1.4301 0.02476 0.01474 -0.2418 0.5147 1.0000
3.000 1.4581 0.02508 0.01490 -0.2421 0.5121 1.0000
3.250 1.4807 0.02560 0.01539 -0.2415 0.5084 1.0000
3.500 1.5023 0.02615 0.01594 -0.2407 0.5044 1.0000
3.750 1.5262 0.02659 0.01634 -0.2403 0.5010 1.0000
4.000 1.5521 0.02696 0.01661 -0.2402 0.4982 1.0000
4.250 1.5798 0.02729 0.01683 -0.2405 0.4959 1.0000
4.500 1.5964 0.02804 0.01768 -0.2390 0.4919 1.0000
4.750 1.6159 0.02865 0.01835 -0.2379 0.4881 1.0000
5.000 1.6384 0.02912 0.01880 -0.2373 0.4849 1.0000
5.250 1.6636 0.02949 0.01912 -0.2371 0.4822 1.0000
5.500 1.6886 0.02993 0.01950 -0.2369 0.4798 1.0000
5.750 1.7001 0.03088 0.02065 -0.2347 0.4758 1.0000
6.000 1.7163 0.03161 0.02145 -0.2331 0.4722 1.0000
6.250 1.7369 0.03213 0.02199 -0.2323 0.4692 1.0000
6.500 1.7616 0.03250 0.02232 -0.2320 0.4666 1.0000
6.750 1.7819 0.03310 0.02299 -0.2312 0.4640 1.0000
7.000 1.7854 0.03436 0.02445 -0.2278 0.4600 1.0000
7.250 1.7959 0.03529 0.02548 -0.2254 0.4565 1.0000
7.500 1.8127 0.03589 0.02613 -0.2240 0.4536 1.0000
7.750 1.8373 0.03624 0.02647 -0.2237 0.4512 1.0000
8.000 1.8471 0.03719 0.02755 -0.2213 0.4483 1.0000
8.250 1.8322 0.03922 0.02981 -0.2155 0.4441 1.0000
8.500 1.8335 0.04064 0.03135 -0.2122 0.4406 1.0000
8.750 1.8489 0.04136 0.03214 -0.2108 0.4378 1.0000
9.000 1.8756 0.04155 0.03234 -0.2108 0.4356 1.0000
9.250 1.8462 0.04491 0.03595 -0.2043 0.4310 1.0000
9.500 1.8135 0.04911 0.04038 -0.1986 0.4259 1.0000
9.750 1.8229 0.05041 0.04178 -0.1970 0.4229 1.0000
10.000 1.8510 0.05026 0.04168 -0.1970 0.4209 1.0000
10.500 1.7399 0.06575 0.05759 -0.1873 0.4063 1.0000
10.750 1.7723 0.06474 0.05664 -0.1870 0.4052 1.0000
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Polar data table (+)
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