WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Reynolds number: 500,000 Max Cl/Cd: 117.1 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx72150b-il-500000.txt Download as CSV file: xf-fx72150b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 72-MS-150B 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.2714 0.10180 0.09788 -0.1547 0.7294 0.0158
-10.750 0.2732 0.09975 0.09577 -0.1566 0.7248 0.0160
-10.500 0.2782 0.09765 0.09369 -0.1580 0.7198 0.0160
-10.250 0.2934 0.09450 0.09051 -0.1580 0.7147 0.0162
-10.000 0.3047 0.09240 0.08835 -0.1583 0.7100 0.0164
-9.750 0.3137 0.09018 0.08614 -0.1592 0.7054 0.0165
-9.500 0.3233 0.08824 0.08419 -0.1600 0.7006 0.0170
-9.250 0.3322 0.08615 0.08207 -0.1608 0.6961 0.0175
-9.000 0.3407 0.08407 0.07995 -0.1616 0.6921 0.0177
-8.750 0.3491 0.08191 0.07781 -0.1625 0.6879 0.0183
-8.500 0.3568 0.07973 0.07562 -0.1634 0.6836 0.0187
-8.250 0.3584 0.07762 0.07350 -0.1652 0.6797 0.0191
-8.000 0.3625 0.07553 0.07139 -0.1665 0.6759 0.0192
-7.750 0.3690 0.07289 0.06878 -0.1673 0.6721 0.0193
-7.500 0.3830 0.07088 0.06676 -0.1668 0.6681 0.0196
-7.250 0.3935 0.06909 0.06494 -0.1671 0.6643 0.0198
-7.000 0.4024 0.06733 0.06313 -0.1674 0.6606 0.0202
-6.750 0.4100 0.06546 0.06130 -0.1679 0.6572 0.0208
-6.500 0.4167 0.06355 0.05942 -0.1683 0.6536 0.0212
-6.250 0.4200 0.06156 0.05744 -0.1685 0.6501 0.0222
-6.000 0.4170 0.05889 0.05478 -0.1718 0.6468 0.0228
-5.750 0.4266 0.05588 0.05174 -0.1751 0.6435 0.0230
-5.500 0.4380 0.05418 0.05007 -0.1747 0.6405 0.0232
-5.250 0.4514 0.05288 0.04878 -0.1745 0.6373 0.0237
-5.000 0.4661 0.05098 0.04688 -0.1764 0.6342 0.0242
-4.750 0.4833 0.04859 0.04446 -0.1798 0.6313 0.0251
-4.500 0.5462 0.03723 0.03278 -0.2090 0.6285 0.0271
-4.250 0.5621 0.03566 0.03130 -0.2089 0.6259 0.0274
-4.000 0.5877 0.03385 0.02946 -0.2118 0.6232 0.0279
-3.750 0.6212 0.03130 0.02680 -0.2171 0.6205 0.0289
-3.500 0.6799 0.02546 0.02041 -0.2297 0.6179 0.0325
-3.250 0.7104 0.02422 0.01909 -0.2320 0.6155 0.0335
-3.000 0.7545 0.02170 0.01610 -0.2374 0.6130 0.0382
-2.750 0.7854 0.02078 0.01512 -0.2391 0.6106 0.0402
-2.500 0.8216 0.01936 0.01344 -0.2419 0.6083 0.0454
-2.250 0.8564 0.01842 0.01223 -0.2440 0.6058 0.0521
-2.000 0.9031 0.01465 0.00761 -0.2470 0.6037 0.0270
-1.500 0.9658 0.01332 0.00612 -0.2491 0.5995 0.0279
-1.250 0.9967 0.01309 0.00584 -0.2500 0.5973 0.0294
-1.000 1.0277 0.01296 0.00565 -0.2509 0.5952 0.0313
-0.750 1.0579 0.01274 0.00547 -0.2518 0.5933 0.0350
-0.500 1.0881 0.01259 0.00531 -0.2526 0.5912 0.0397
-0.250 1.1179 0.01250 0.00522 -0.2533 0.5891 0.0480
0.000 1.1495 0.01227 0.00514 -0.2545 0.5870 0.1104
0.250 1.1833 0.01178 0.00537 -0.2567 0.5851 0.4654
0.500 1.2113 0.01191 0.00550 -0.2569 0.5833 0.5074
0.750 1.2395 0.01210 0.00565 -0.2572 0.5815 0.5314
1.000 1.2680 0.01235 0.00585 -0.2576 0.5795 0.5514
1.250 1.2946 0.01248 0.00601 -0.2576 0.5780 0.5682
1.500 1.3212 0.01263 0.00619 -0.2576 0.5764 0.5862
1.750 1.3481 0.01277 0.00634 -0.2577 0.5748 0.5971
2.000 1.3754 0.01292 0.00648 -0.2578 0.5732 0.6061
2.250 1.4027 0.01304 0.00661 -0.2581 0.5716 0.6129
2.500 1.4302 0.01317 0.00674 -0.2583 0.5702 0.6189
2.750 1.4578 0.01332 0.00686 -0.2587 0.5688 0.6243
3.000 1.4854 0.01346 0.00700 -0.2590 0.5675 0.6291
3.250 1.5134 0.01364 0.00717 -0.2594 0.5661 0.6342
3.500 1.5422 0.01388 0.00738 -0.2600 0.5646 0.6398
3.750 1.5697 0.01409 0.00761 -0.2604 0.5634 0.6449
4.000 1.5955 0.01424 0.00783 -0.2604 0.5623 0.6510
4.250 1.6213 0.01442 0.00805 -0.2604 0.5609 0.6580
4.500 1.6470 0.01457 0.00827 -0.2605 0.5595 0.6651
4.750 1.6729 0.01474 0.00849 -0.2606 0.5579 0.6737
5.000 1.6990 0.01490 0.00872 -0.2607 0.5564 0.6821
5.250 1.7253 0.01508 0.00894 -0.2608 0.5551 0.6923
5.500 1.7518 0.01526 0.00917 -0.2611 0.5538 0.7041
5.750 1.7786 0.01543 0.00940 -0.2614 0.5526 0.7185
6.000 1.8058 0.01562 0.00966 -0.2617 0.5515 0.7381
6.250 1.8331 0.01579 0.00994 -0.2622 0.5503 0.7750
6.500 1.8561 0.01585 0.01020 -0.2616 0.5489 1.0000
6.750 1.8825 0.01620 0.01059 -0.2619 0.5476 1.0000
7.000 1.9044 0.01645 0.01092 -0.2613 0.5462 1.0000
7.250 1.9262 0.01670 0.01125 -0.2607 0.5445 1.0000
7.500 1.9474 0.01692 0.01154 -0.2600 0.5421 1.0000
7.750 1.9690 0.01704 0.01169 -0.2593 0.5390 1.0000
8.000 1.9932 0.01715 0.01180 -0.2590 0.5361 1.0000
8.250 2.0196 0.01736 0.01202 -0.2593 0.5335 1.0000
8.500 2.0398 0.01768 0.01239 -0.2584 0.5305 1.0000
8.750 2.0506 0.01792 0.01276 -0.2558 0.5272 1.0000
9.000 2.0635 0.01814 0.01305 -0.2535 0.5239 1.0000
9.250 2.0786 0.01831 0.01325 -0.2515 0.5206 1.0000
9.500 2.1025 0.01846 0.01336 -0.2513 0.5160 1.0000
9.750 2.0951 0.01902 0.01408 -0.2455 0.5123 1.0000
10.000 2.0954 0.01958 0.01472 -0.2414 0.5073 1.0000
10.250 2.1046 0.02000 0.01512 -0.2388 0.5014 1.0000
10.500 2.1004 0.02105 0.01631 -0.2345 0.4959 1.0000
10.750 2.1014 0.02205 0.01738 -0.2311 0.4896 1.0000
11.000 2.1084 0.02298 0.01834 -0.2287 0.4839 1.0000
11.250 2.1073 0.02441 0.01989 -0.2255 0.4772 1.0000
11.500 2.1100 0.02572 0.02120 -0.2228 0.4696 1.0000
11.750 2.1060 0.02762 0.02324 -0.2196 0.4599 1.0000
12.000 2.1026 0.02961 0.02530 -0.2166 0.4490 1.0000
12.250 2.0949 0.03209 0.02782 -0.2133 0.4339 1.0000
12.500 2.0785 0.03547 0.03116 -0.2095 0.4161 1.0000
12.750 2.0579 0.03954 0.03518 -0.2056 0.3970 1.0000
13.000 2.0320 0.04445 0.04003 -0.2017 0.3693 1.0000
13.250 2.0007 0.05026 0.04574 -0.1979 0.3490 1.0000
13.500 1.9743 0.05585 0.05129 -0.1948 0.3295 1.0000
13.750 1.9471 0.06179 0.05717 -0.1920 0.3065 1.0000
14.000 1.9193 0.06810 0.06340 -0.1895 0.2858 1.0000
14.250 1.8948 0.07422 0.06947 -0.1875 0.2653 1.0000
14.500 1.8704 0.08052 0.07568 -0.1857 0.2421 1.0000
14.750 1.8464 0.08695 0.08201 -0.1843 0.2191 1.0000
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