WORTMANN FX 3 AIRFOIL (fx3-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 3 AIRFOIL (fx3-il) Reynolds number: 200,000 Max Cl/Cd: 32.94 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx3-il-200000-n5.txt Download as CSV file: xf-fx3-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 3 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.4560 0.08915 0.08422 -0.1410 0.8350 0.0170
-16.000 -0.4944 0.07879 0.07359 -0.1469 0.8352 0.0168
-15.750 -0.5181 0.07197 0.06654 -0.1504 0.8353 0.0168
-15.500 -0.5347 0.06672 0.06107 -0.1526 0.8353 0.0170
-15.250 -0.5468 0.06243 0.05656 -0.1540 0.8354 0.0172
-15.000 -0.5551 0.05884 0.05276 -0.1548 0.8355 0.0174
-14.750 -0.5602 0.05576 0.04946 -0.1552 0.8356 0.0177
-14.500 -0.5620 0.05312 0.04660 -0.1554 0.8356 0.0181
-14.250 -0.5607 0.05085 0.04409 -0.1553 0.8357 0.0184
-14.000 -0.5574 0.04889 0.04199 -0.1551 0.8358 0.0189
-13.750 -0.5519 0.04734 0.04038 -0.1550 0.8358 0.0195
-13.500 -0.5445 0.04606 0.03903 -0.1548 0.8359 0.0201
-13.250 -0.5358 0.04491 0.03780 -0.1546 0.8359 0.0208
-13.000 -0.5260 0.04380 0.03658 -0.1542 0.8360 0.0217
-12.750 -0.5151 0.04273 0.03537 -0.1538 0.8361 0.0226
-12.500 -0.5025 0.04174 0.03422 -0.1533 0.8362 0.0236
-12.250 -0.4905 0.04081 0.03322 -0.1527 0.8362 0.0245
-12.000 -0.4792 0.04011 0.03248 -0.1521 0.8363 0.0255
-11.750 -0.4669 0.03956 0.03187 -0.1515 0.8363 0.0269
-11.500 -0.4533 0.03899 0.03122 -0.1507 0.8360 0.0286
-11.250 -0.4384 0.03848 0.03058 -0.1499 0.8359 0.0304
-11.000 -0.4270 0.03803 0.03013 -0.1489 0.8359 0.0320
-10.750 -0.4154 0.03774 0.02982 -0.1478 0.8359 0.0338
-10.500 -0.4036 0.03754 0.02956 -0.1465 0.8359 0.0361
-10.250 -0.3918 0.03741 0.02931 -0.1450 0.8358 0.0386
-10.000 -0.3852 0.03728 0.02922 -0.1429 0.8358 0.0406
-9.750 -0.3794 0.03733 0.02925 -0.1405 0.8357 0.0427
-9.500 -0.3757 0.03747 0.02936 -0.1375 0.8356 0.0450
-9.250 -0.3752 0.03776 0.02957 -0.1338 0.8355 0.0470
-9.000 -0.3709 0.03765 0.02949 -0.1308 0.8350 0.0492
-8.750 -0.3681 0.03771 0.02954 -0.1275 0.8347 0.0513
-8.500 -0.3732 0.03801 0.02983 -0.1227 0.8344 0.0531
-8.250 -0.5017 0.04031 0.03215 -0.0951 0.8315 0.0473
-8.000 -0.5318 0.04048 0.03231 -0.0859 0.8304 0.0475
-7.750 -0.5550 0.04034 0.03218 -0.0778 0.8284 0.0481
-7.500 -0.5703 0.04012 0.03197 -0.0712 0.8272 0.0491
-7.250 -0.5741 0.03985 0.03169 -0.0667 0.8262 0.0508
-7.000 -0.5672 0.03952 0.03132 -0.0641 0.8249 0.0533
-6.750 -0.5533 0.03920 0.03092 -0.0626 0.8236 0.0563
-6.500 -0.5412 0.03879 0.03047 -0.0610 0.8227 0.0589
-6.250 -0.5262 0.03838 0.03007 -0.0600 0.8220 0.0621
-6.000 -0.5069 0.03808 0.02973 -0.0596 0.8213 0.0656
-5.750 -0.4823 0.03785 0.02942 -0.0600 0.8205 0.0694
-5.500 -0.4570 0.03737 0.02893 -0.0609 0.8198 0.0736
-5.250 -0.4676 0.03696 0.02854 -0.0557 0.8146 0.0753
-5.000 -0.4492 0.03658 0.02814 -0.0555 0.8123 0.0793
-4.750 -0.4249 0.03627 0.02776 -0.0562 0.8106 0.0833
-4.500 -0.3966 0.03588 0.02735 -0.0577 0.8092 0.0883
-4.250 -0.3662 0.03554 0.02701 -0.0596 0.8081 0.0964
-4.000 -0.3339 0.03522 0.02673 -0.0619 0.8072 0.1109
-3.750 -0.2960 0.03446 0.02633 -0.0662 0.8066 0.1764
-3.500 -0.2759 0.03485 0.02898 -0.0640 0.8058 0.5491
-3.250 -0.2979 0.03653 0.03085 -0.0520 0.7985 0.5740
-2.750 -0.2123 0.03740 0.03138 -0.0618 0.7955 0.6586
-2.500 -0.1819 0.03798 0.03186 -0.0626 0.7943 0.6686
-2.000 -0.1261 0.03909 0.03282 -0.0620 0.7923 0.6812
-1.750 -0.1268 0.03951 0.03325 -0.0571 0.7855 0.6844
-1.500 -0.0948 0.03975 0.03339 -0.0590 0.7834 0.6931
-1.250 -0.0791 0.04025 0.03389 -0.0553 0.7815 0.6960
-1.000 -0.0559 0.04063 0.03425 -0.0538 0.7803 0.7005
-0.750 -0.0162 0.04066 0.03416 -0.0576 0.7796 0.7073
-0.500 -0.0111 0.04073 0.03423 -0.0543 0.7726 0.7084
-0.250 0.0156 0.04070 0.03416 -0.0547 0.7706 0.7093
0.000 0.0448 0.04065 0.03407 -0.0554 0.7691 0.7104
0.250 0.0758 0.04060 0.03397 -0.0565 0.7680 0.7116
0.500 0.1087 0.04053 0.03386 -0.0581 0.7672 0.7128
0.750 0.1181 0.04060 0.03394 -0.0563 0.7593 0.7143
1.000 0.1507 0.04051 0.03381 -0.0581 0.7577 0.7157
1.250 0.1857 0.04041 0.03367 -0.0604 0.7566 0.7173
1.500 0.2229 0.04028 0.03351 -0.0632 0.7557 0.7187
1.750 0.2407 0.04040 0.03362 -0.0636 0.7478 0.7204
2.000 0.2767 0.04028 0.03348 -0.0663 0.7461 0.7217
2.250 0.3079 0.04010 0.03330 -0.0673 0.7448 0.7222
2.750 0.3509 0.04004 0.03329 -0.0668 0.7348 0.7232
3.000 0.3821 0.03982 0.03309 -0.0679 0.7331 0.7238
3.500 0.4265 0.03982 0.03314 -0.0677 0.7224 0.7251
3.750 0.4587 0.03956 0.03292 -0.0690 0.7206 0.7257
4.250 0.5064 0.03961 0.03305 -0.0696 0.7093 0.7268
4.500 0.5402 0.03929 0.03278 -0.0713 0.7074 0.7270
5.000 0.5898 0.03937 0.03298 -0.0721 0.6958 0.7281
5.250 0.6232 0.03903 0.03269 -0.0737 0.6935 0.7284
5.750 0.6758 0.03904 0.03284 -0.0751 0.6814 0.7287
6.000 0.7094 0.03859 0.03246 -0.0766 0.6784 0.7289
6.500 0.7636 0.03839 0.03243 -0.0779 0.6648 0.7291
6.750 0.7952 0.03791 0.03201 -0.0789 0.6576 0.7292
7.000 0.8322 0.03673 0.03087 -0.0803 0.6424 0.7294
7.250 0.8742 0.03525 0.02938 -0.0823 0.6216 0.7299
7.500 0.9173 0.03399 0.02814 -0.0847 0.6060 0.7303
7.750 0.9624 0.03262 0.02675 -0.0873 0.5843 0.7304
8.000 1.0015 0.03169 0.02574 -0.0891 0.5558 0.7305
8.250 1.0309 0.03130 0.02513 -0.0895 0.5111 0.7306
8.500 1.0430 0.03198 0.02548 -0.0877 0.4548 0.7306
8.750 1.0453 0.03336 0.02651 -0.0847 0.3959 0.7306
9.000 1.0450 0.03503 0.02782 -0.0816 0.3357 0.7306
9.250 1.0453 0.03678 0.02923 -0.0788 0.2764 0.7306
9.500 1.0470 0.03854 0.03067 -0.0763 0.2215 0.7306
9.750 1.0522 0.04015 0.03200 -0.0743 0.1756 0.7305
10.000 1.0605 0.04160 0.03327 -0.0728 0.1409 0.7306
10.250 1.0714 0.04290 0.03445 -0.0716 0.1177 0.7306
10.500 1.0839 0.04412 0.03561 -0.0707 0.1015 0.7306
10.750 1.0968 0.04532 0.03678 -0.0698 0.0877 0.7306
11.000 1.1101 0.04650 0.03795 -0.0690 0.0755 0.7306
11.250 1.1231 0.04773 0.03916 -0.0681 0.0634 0.7306
11.500 1.1347 0.04909 0.04051 -0.0672 0.0508 0.7306
11.750 1.1459 0.05050 0.04190 -0.0662 0.0401 0.7307
12.000 1.1562 0.05200 0.04338 -0.0652 0.0332 0.7309
12.250 1.1663 0.05353 0.04494 -0.0641 0.0290 0.7311
12.500 1.1755 0.05518 0.04663 -0.0631 0.0264 0.7313
12.750 1.1859 0.05675 0.04830 -0.0622 0.0245 0.7313
13.000 1.1950 0.05847 0.05010 -0.0612 0.0230 0.7313
13.250 1.2022 0.06039 0.05210 -0.0602 0.0217 0.7313
13.500 1.2068 0.06258 0.05438 -0.0590 0.0206 0.7312
13.750 1.2152 0.06444 0.05637 -0.0582 0.0198 0.7312
14.000 1.2230 0.06638 0.05843 -0.0575 0.0189 0.7312
14.250 1.2296 0.06847 0.06063 -0.0567 0.0181 0.7312
14.500 1.2356 0.07065 0.06291 -0.0560 0.0174 0.7312
14.750 1.2403 0.07300 0.06536 -0.0553 0.0169 0.7312
15.000 1.2434 0.07555 0.06799 -0.0546 0.0164 0.7312
15.250 1.2442 0.07831 0.07083 -0.0538 0.0159 0.7312
15.500 1.2491 0.08070 0.07336 -0.0533 0.0156 0.7312
15.750 1.2546 0.08308 0.07588 -0.0529 0.0152 0.7312
16.000 1.2592 0.08558 0.07853 -0.0526 0.0148 0.7312
16.250 1.2634 0.08816 0.08124 -0.0524 0.0143 0.7312
16.500 1.2668 0.09086 0.08407 -0.0524 0.0139 0.7312
16.750 1.2696 0.09367 0.08700 -0.0524 0.0135 0.7312
17.000 1.2718 0.09657 0.09001 -0.0526 0.0132 0.7312
17.250 1.2733 0.09959 0.09313 -0.0529 0.0129 0.7312
17.500 1.2744 0.10267 0.09630 -0.0533 0.0126 0.7312
17.750 1.2753 0.10577 0.09949 -0.0537 0.0124 0.7313
18.000 1.2756 0.10889 0.10272 -0.0541 0.0122 0.7313
18.250 1.2754 0.11238 0.10640 -0.0550 0.0121 0.7313
18.500 1.2736 0.11618 0.11040 -0.0561 0.0119 0.7313
18.750 1.2708 0.12020 0.11462 -0.0575 0.0117 0.7313
19.000 1.2667 0.12448 0.11910 -0.0591 0.0116 0.7313
19.250 1.2615 0.12909 0.12391 -0.0612 0.0114 0.7313
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 3 AIRFOIL (fx3-il)