WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 71-089A AIRFOIL (fx71089a-il) Reynolds number: 200,000 Max Cl/Cd: 36.39 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx71089a-il-200000-n5.txt Download as CSV file: xf-fx71089a-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.9646 0.05815 0.05324 -0.0350 1.0000 0.0431
-12.000 -0.9834 0.05419 0.04914 -0.0358 1.0000 0.0433
-11.750 -0.9978 0.05122 0.04603 -0.0346 1.0000 0.0435
-11.500 -1.0074 0.04887 0.04353 -0.0323 1.0000 0.0437
-11.250 -1.0108 0.04644 0.04093 -0.0305 1.0000 0.0440
-11.000 -1.0109 0.04396 0.03824 -0.0289 1.0000 0.0443
-10.750 -1.0063 0.04173 0.03580 -0.0273 1.0000 0.0446
-10.500 -0.9984 0.03970 0.03358 -0.0258 1.0000 0.0451
-10.250 -0.9884 0.03780 0.03147 -0.0243 1.0000 0.0456
-10.000 -0.9773 0.03584 0.02926 -0.0229 1.0000 0.0461
-9.750 -0.9650 0.03385 0.02700 -0.0214 1.0000 0.0465
-9.500 -0.9507 0.03201 0.02489 -0.0201 1.0000 0.0468
-9.250 -0.9346 0.03036 0.02298 -0.0188 1.0000 0.0472
-9.000 -0.9169 0.02886 0.02126 -0.0175 1.0000 0.0476
-8.750 -0.8981 0.02750 0.01968 -0.0164 1.0000 0.0479
-8.500 -0.8782 0.02627 0.01824 -0.0152 1.0000 0.0483
-8.250 -0.8576 0.02520 0.01698 -0.0141 1.0000 0.0487
-8.000 -0.8364 0.02416 0.01580 -0.0131 1.0000 0.0492
-7.750 -0.8146 0.02315 0.01476 -0.0122 1.0000 0.0497
-7.500 -0.7925 0.02231 0.01388 -0.0113 1.0000 0.0503
-7.250 -0.7702 0.02151 0.01304 -0.0103 1.0000 0.0507
-7.000 -0.7478 0.02075 0.01224 -0.0094 1.0000 0.0512
-6.750 -0.7254 0.02003 0.01148 -0.0084 1.0000 0.0517
-6.500 -0.7029 0.01935 0.01076 -0.0073 1.0000 0.0522
-6.250 -0.6805 0.01870 0.01008 -0.0062 1.0000 0.0528
-6.000 -0.6581 0.01809 0.00943 -0.0051 1.0000 0.0534
-5.750 -0.6357 0.01750 0.00882 -0.0040 1.0000 0.0541
-5.500 -0.6134 0.01696 0.00826 -0.0029 1.0000 0.0548
-5.250 -0.5908 0.01648 0.00774 -0.0017 1.0000 0.0557
-5.000 -0.5688 0.01596 0.00723 -0.0005 1.0000 0.0566
-4.750 -0.5470 0.01546 0.00677 0.0007 1.0000 0.0577
-4.500 -0.5249 0.01504 0.00637 0.0018 1.0000 0.0588
-4.250 -0.5028 0.01464 0.00599 0.0031 1.0000 0.0600
-4.000 -0.4808 0.01427 0.00562 0.0043 1.0000 0.0614
-3.750 -0.4587 0.01393 0.00528 0.0055 1.0000 0.0630
-3.500 -0.4366 0.01362 0.00497 0.0068 1.0000 0.0646
-3.250 -0.4152 0.01325 0.00466 0.0081 1.0000 0.0670
-3.000 -0.3934 0.01296 0.00441 0.0093 1.0000 0.0704
-2.750 -0.3717 0.01270 0.00418 0.0106 1.0000 0.0751
-2.500 -0.3475 0.01240 0.00398 0.0113 0.9990 0.0835
-2.250 -0.3104 0.01206 0.00381 0.0093 0.9930 0.1041
-2.000 -0.2748 0.01172 0.00364 0.0076 0.9861 0.1337
-1.750 -0.2387 0.01134 0.00350 0.0058 0.9782 0.1751
-1.500 -0.2005 0.01091 0.00337 0.0036 0.9677 0.2334
-1.250 -0.1622 0.01039 0.00322 0.0015 0.9550 0.3112
-1.000 -0.1285 0.00977 0.00312 0.0003 0.9405 0.4235
-0.750 -0.0955 0.00924 0.00305 -0.0005 0.9225 0.5282
-0.500 -0.0628 0.00875 0.00300 -0.0009 0.8949 0.6331
-0.250 -0.0307 0.00839 0.00300 -0.0007 0.8566 0.7368
0.000 0.0000 0.00828 0.00301 0.0000 0.8058 0.8057
0.250 0.0306 0.00839 0.00300 0.0007 0.7368 0.8562
0.500 0.0629 0.00875 0.00300 0.0009 0.6333 0.8950
0.750 0.0955 0.00924 0.00305 0.0005 0.5278 0.9222
1.000 0.1284 0.00977 0.00312 -0.0002 0.4237 0.9405
1.250 0.1623 0.01038 0.00322 -0.0015 0.3125 0.9550
1.500 0.2005 0.01091 0.00337 -0.0036 0.2324 0.9678
1.750 0.2387 0.01134 0.00350 -0.0058 0.1757 0.9782
2.000 0.2748 0.01171 0.00364 -0.0076 0.1346 0.9862
2.250 0.3104 0.01206 0.00381 -0.0093 0.1043 0.9930
2.500 0.3475 0.01240 0.00398 -0.0113 0.0834 0.9991
2.750 0.3717 0.01270 0.00417 -0.0106 0.0751 1.0000
3.000 0.3934 0.01296 0.00441 -0.0093 0.0703 1.0000
3.250 0.4151 0.01325 0.00466 -0.0081 0.0669 1.0000
3.500 0.4365 0.01362 0.00497 -0.0068 0.0645 1.0000
3.750 0.4586 0.01393 0.00528 -0.0055 0.0629 1.0000
4.000 0.4807 0.01427 0.00562 -0.0043 0.0614 1.0000
4.250 0.5028 0.01464 0.00598 -0.0031 0.0600 1.0000
4.500 0.5249 0.01503 0.00636 -0.0018 0.0588 1.0000
4.750 0.5470 0.01546 0.00677 -0.0007 0.0577 1.0000
5.000 0.5688 0.01596 0.00723 0.0005 0.0566 1.0000
5.250 0.5908 0.01648 0.00773 0.0017 0.0557 1.0000
5.500 0.6133 0.01696 0.00825 0.0029 0.0548 1.0000
5.750 0.6357 0.01750 0.00882 0.0040 0.0541 1.0000
6.000 0.6580 0.01808 0.00943 0.0051 0.0534 1.0000
6.250 0.6805 0.01870 0.01008 0.0062 0.0528 1.0000
6.500 0.7029 0.01935 0.01076 0.0073 0.0522 1.0000
6.750 0.7254 0.02003 0.01148 0.0084 0.0517 1.0000
7.000 0.7478 0.02075 0.01224 0.0094 0.0512 1.0000
7.250 0.7702 0.02150 0.01304 0.0103 0.0507 1.0000
7.500 0.7925 0.02230 0.01388 0.0113 0.0503 1.0000
7.750 0.8146 0.02314 0.01474 0.0122 0.0497 1.0000
8.000 0.8364 0.02416 0.01580 0.0131 0.0492 1.0000
8.250 0.8576 0.02520 0.01697 0.0141 0.0487 1.0000
8.500 0.8782 0.02628 0.01824 0.0152 0.0483 1.0000
8.750 0.8981 0.02751 0.01969 0.0163 0.0479 1.0000
9.000 0.9170 0.02886 0.02126 0.0175 0.0476 1.0000
9.250 0.9346 0.03036 0.02299 0.0187 0.0472 1.0000
9.500 0.9508 0.03202 0.02490 0.0200 0.0468 1.0000
9.750 0.9651 0.03386 0.02701 0.0214 0.0465 1.0000
10.000 0.9775 0.03584 0.02925 0.0229 0.0461 1.0000
10.250 0.9885 0.03781 0.03148 0.0243 0.0456 1.0000
10.500 0.9984 0.03975 0.03363 0.0258 0.0451 1.0000
10.750 1.0067 0.04171 0.03578 0.0272 0.0446 1.0000
11.000 1.0107 0.04403 0.03830 0.0288 0.0443 1.0000
11.250 1.0108 0.04651 0.04100 0.0305 0.0440 1.0000
11.500 1.0073 0.04893 0.04359 0.0323 0.0438 1.0000
11.750 1.0004 0.05107 0.04585 0.0345 0.0435 1.0000
12.000 0.9937 0.05335 0.04822 0.0358 0.0432 1.0000
12.250 0.9773 0.05692 0.05193 0.0357 0.0430 1.0000
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