WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Reynolds number: 500,000 Max Cl/Cd: 52.31 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx71089a-il-500000-n5.txt Download as CSV file: xf-fx71089a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-089A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.2148 0.05550 0.05176 -0.0372 1.0000 0.0291
-15.250 -1.2248 0.05067 0.04678 -0.0406 1.0000 0.0294
-15.000 -1.2350 0.04638 0.04234 -0.0429 1.0000 0.0296
-14.750 -1.2420 0.04304 0.03885 -0.0441 1.0000 0.0298
-14.500 -1.2474 0.04029 0.03595 -0.0443 1.0000 0.0300
-14.250 -1.2496 0.03818 0.03370 -0.0437 1.0000 0.0304
-14.000 -1.2521 0.03622 0.03159 -0.0423 1.0000 0.0306
-13.750 -1.2527 0.03462 0.02983 -0.0403 1.0000 0.0309
-13.500 -1.2518 0.03323 0.02829 -0.0379 1.0000 0.0312
-13.250 -1.2494 0.03203 0.02691 -0.0352 1.0000 0.0316
-13.000 -1.2416 0.03096 0.02567 -0.0330 1.0000 0.0319
-12.750 -1.2303 0.02999 0.02455 -0.0312 1.0000 0.0321
-12.500 -1.2179 0.02885 0.02334 -0.0297 1.0000 0.0325
-12.250 -1.2022 0.02805 0.02251 -0.0283 1.0000 0.0328
-12.000 -1.1850 0.02740 0.02182 -0.0271 1.0000 0.0331
-11.750 -1.1672 0.02677 0.02114 -0.0259 1.0000 0.0335
-11.500 -1.1487 0.02617 0.02048 -0.0247 1.0000 0.0340
-11.250 -1.1302 0.02546 0.01969 -0.0236 1.0000 0.0344
-11.000 -1.1115 0.02470 0.01883 -0.0224 1.0000 0.0348
-10.750 -1.0923 0.02396 0.01798 -0.0213 1.0000 0.0352
-10.500 -1.0724 0.02328 0.01720 -0.0202 1.0000 0.0357
-10.250 -1.0519 0.02264 0.01646 -0.0191 1.0000 0.0361
-10.000 -1.0309 0.02207 0.01577 -0.0181 1.0000 0.0366
-9.750 -1.0097 0.02147 0.01507 -0.0171 1.0000 0.0368
-9.500 -0.9884 0.02080 0.01431 -0.0161 1.0000 0.0370
-9.250 -0.9675 0.01998 0.01341 -0.0150 1.0000 0.0372
-9.000 -0.9468 0.01908 0.01246 -0.0139 1.0000 0.0375
-8.750 -0.9256 0.01833 0.01167 -0.0128 1.0000 0.0378
-8.500 -0.9040 0.01768 0.01099 -0.0117 1.0000 0.0381
-8.250 -0.8821 0.01711 0.01039 -0.0107 1.0000 0.0383
-8.000 -0.8601 0.01658 0.00983 -0.0096 1.0000 0.0386
-7.750 -0.8379 0.01608 0.00930 -0.0085 1.0000 0.0389
-7.500 -0.8156 0.01560 0.00879 -0.0074 1.0000 0.0392
-7.250 -0.7931 0.01515 0.00833 -0.0064 1.0000 0.0396
-7.000 -0.7705 0.01474 0.00789 -0.0053 1.0000 0.0400
-6.750 -0.7479 0.01433 0.00746 -0.0042 1.0000 0.0404
-6.500 -0.7253 0.01392 0.00703 -0.0031 1.0000 0.0407
-6.250 -0.7028 0.01354 0.00662 -0.0020 1.0000 0.0411
-6.000 -0.6802 0.01317 0.00624 -0.0008 1.0000 0.0414
-5.750 -0.6575 0.01282 0.00587 0.0003 1.0000 0.0417
-5.500 -0.6349 0.01249 0.00553 0.0015 1.0000 0.0420
-5.250 -0.6123 0.01219 0.00521 0.0027 1.0000 0.0424
-5.000 -0.5897 0.01191 0.00492 0.0038 1.0000 0.0426
-4.750 -0.5678 0.01156 0.00458 0.0051 1.0000 0.0431
-4.500 -0.5423 0.01123 0.00426 0.0056 0.9993 0.0438
-4.250 -0.5087 0.01093 0.00398 0.0045 0.9964 0.0445
-4.000 -0.4746 0.01067 0.00374 0.0032 0.9932 0.0454
-3.750 -0.4417 0.01042 0.00351 0.0022 0.9888 0.0464
-3.500 -0.4071 0.01020 0.00331 0.0009 0.9846 0.0475
-3.250 -0.3742 0.00998 0.00311 0.0000 0.9799 0.0485
-3.000 -0.3414 0.00976 0.00292 -0.0009 0.9733 0.0499
-2.750 -0.3071 0.00954 0.00274 -0.0020 0.9655 0.0520
-2.500 -0.2692 0.00932 0.00257 -0.0040 0.9559 0.0553
-2.250 -0.2316 0.00909 0.00240 -0.0058 0.9409 0.0622
-2.000 -0.1941 0.00887 0.00221 -0.0075 0.9147 0.0730
-1.750 -0.1627 0.00866 0.00203 -0.0079 0.8714 0.0961
-1.500 -0.1379 0.00860 0.00189 -0.0068 0.8128 0.1217
-1.250 -0.1145 0.00860 0.00178 -0.0055 0.7556 0.1439
-1.000 -0.0913 0.00859 0.00168 -0.0043 0.6945 0.1769
-0.750 -0.0697 0.00869 0.00160 -0.0028 0.6028 0.2205
-0.500 -0.0469 0.00878 0.00155 -0.0017 0.5199 0.2638
-0.250 -0.0236 0.00886 0.00152 -0.0008 0.4424 0.3125
0.000 0.0000 0.00892 0.00152 0.0000 0.3679 0.3673
0.250 0.0236 0.00886 0.00152 0.0008 0.3129 0.4422
0.500 0.0470 0.00879 0.00155 0.0017 0.2643 0.5177
1.000 0.0914 0.00859 0.00168 0.0042 0.1770 0.6934
1.250 0.1144 0.00859 0.00178 0.0055 0.1440 0.7568
1.500 0.1379 0.00860 0.00189 0.0068 0.1211 0.8139
1.750 0.1627 0.00866 0.00204 0.0079 0.0957 0.8720
2.000 0.1939 0.00886 0.00221 0.0076 0.0734 0.9140
2.250 0.2317 0.00909 0.00240 0.0058 0.0623 0.9410
2.500 0.2690 0.00932 0.00257 0.0040 0.0553 0.9558
2.750 0.3071 0.00953 0.00274 0.0020 0.0520 0.9656
3.000 0.3413 0.00976 0.00292 0.0009 0.0498 0.9732
3.250 0.3742 0.00998 0.00311 0.0000 0.0485 0.9799
3.500 0.4072 0.01020 0.00331 -0.0010 0.0475 0.9846
3.750 0.4417 0.01042 0.00351 -0.0022 0.0464 0.9889
4.000 0.4746 0.01067 0.00374 -0.0032 0.0453 0.9932
4.250 0.5087 0.01093 0.00398 -0.0045 0.0445 0.9964
4.500 0.5423 0.01123 0.00426 -0.0057 0.0437 0.9993
4.750 0.5677 0.01156 0.00458 -0.0051 0.0431 1.0000
5.000 0.5897 0.01191 0.00492 -0.0038 0.0426 1.0000
5.250 0.6122 0.01219 0.00521 -0.0026 0.0423 1.0000
5.500 0.6349 0.01249 0.00553 -0.0015 0.0420 1.0000
5.750 0.6575 0.01282 0.00587 -0.0003 0.0417 1.0000
6.000 0.6801 0.01317 0.00623 0.0008 0.0414 1.0000
6.250 0.7027 0.01353 0.00662 0.0020 0.0411 1.0000
6.500 0.7253 0.01392 0.00703 0.0031 0.0407 1.0000
6.750 0.7478 0.01433 0.00745 0.0042 0.0404 1.0000
7.000 0.7704 0.01474 0.00789 0.0053 0.0400 1.0000
7.250 0.7930 0.01516 0.00833 0.0064 0.0396 1.0000
7.500 0.8155 0.01560 0.00879 0.0075 0.0392 1.0000
7.750 0.8378 0.01607 0.00930 0.0085 0.0389 1.0000
8.000 0.8600 0.01658 0.00983 0.0096 0.0386 1.0000
8.250 0.8821 0.01711 0.01039 0.0107 0.0383 1.0000
8.500 0.9040 0.01769 0.01100 0.0117 0.0380 1.0000
8.750 0.9256 0.01834 0.01168 0.0128 0.0378 1.0000
9.000 0.9469 0.01908 0.01246 0.0139 0.0375 1.0000
9.250 0.9674 0.02001 0.01344 0.0150 0.0372 1.0000
9.500 0.9885 0.02081 0.01432 0.0160 0.0370 1.0000
9.750 1.0099 0.02146 0.01506 0.0171 0.0368 1.0000
10.000 1.0311 0.02205 0.01575 0.0181 0.0365 1.0000
10.250 1.0522 0.02259 0.01640 0.0191 0.0361 1.0000
10.500 1.0727 0.02324 0.01716 0.0202 0.0356 1.0000
10.750 1.0926 0.02394 0.01796 0.0212 0.0352 1.0000
11.000 1.1117 0.02471 0.01884 0.0224 0.0348 1.0000
11.250 1.1304 0.02549 0.01972 0.0235 0.0344 1.0000
11.500 1.1489 0.02619 0.02050 0.0247 0.0340 1.0000
11.750 1.1671 0.02686 0.02124 0.0259 0.0336 1.0000
12.000 1.1856 0.02736 0.02178 0.0270 0.0331 1.0000
12.250 1.2027 0.02803 0.02249 0.0282 0.0328 1.0000
12.500 1.2184 0.02883 0.02332 0.0296 0.0325 1.0000
12.750 1.2307 0.03001 0.02457 0.0311 0.0321 1.0000
13.000 1.2419 0.03100 0.02572 0.0329 0.0319 1.0000
13.250 1.2500 0.03204 0.02692 0.0350 0.0316 1.0000
13.500 1.2524 0.03326 0.02831 0.0378 0.0313 1.0000
13.750 1.2534 0.03464 0.02985 0.0402 0.0310 1.0000
14.000 1.2526 0.03627 0.03164 0.0422 0.0307 1.0000
14.250 1.2511 0.03811 0.03363 0.0435 0.0303 1.0000
14.500 1.2481 0.04032 0.03599 0.0441 0.0300 1.0000
14.750 1.2437 0.04297 0.03878 0.0440 0.0298 1.0000
15.000 1.2365 0.04633 0.04229 0.0428 0.0296 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 71-089A AIRFOIL (fx71089a-il)