FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-097 (fx84w097-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.12 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w097-il-1000000-n5.txt Download as CSV file: xf-fx84w097-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-097
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.9340 0.03928 0.03725 -0.0535 1.0000 0.0056
-12.000 -0.9462 0.03377 0.03141 -0.0543 1.0000 0.0056
-11.750 -0.9429 0.03037 0.02774 -0.0542 1.0000 0.0057
-11.500 -0.9302 0.02770 0.02481 -0.0545 0.9795 0.0057
-11.250 -0.9111 0.02571 0.02256 -0.0551 0.9450 0.0058
-11.000 -0.8973 0.02413 0.02072 -0.0539 0.9229 0.0058
-10.750 -0.8804 0.02278 0.01913 -0.0530 0.9072 0.0059
-10.500 -0.8634 0.02123 0.01733 -0.0521 0.8939 0.0059
-10.250 -0.8454 0.01964 0.01548 -0.0514 0.8822 0.0061
-9.750 -0.8015 0.01765 0.01315 -0.0504 0.8611 0.0065
-9.500 -0.7776 0.01693 0.01230 -0.0501 0.8519 0.0067
-9.250 -0.7533 0.01628 0.01152 -0.0498 0.8430 0.0068
-9.000 -0.7284 0.01567 0.01078 -0.0495 0.8345 0.0070
-8.750 -0.7033 0.01509 0.01007 -0.0493 0.8266 0.0072
-8.500 -0.6778 0.01451 0.00939 -0.0490 0.8185 0.0075
-8.250 -0.6520 0.01401 0.00878 -0.0488 0.8112 0.0078
-8.000 -0.6259 0.01355 0.00821 -0.0487 0.8035 0.0081
-7.750 -0.5995 0.01315 0.00771 -0.0485 0.7964 0.0083
-7.500 -0.5728 0.01278 0.00723 -0.0484 0.7890 0.0085
-7.250 -0.5471 0.01212 0.00647 -0.0482 0.7822 0.0091
-7.000 -0.5203 0.01172 0.00600 -0.0481 0.7748 0.0095
-6.750 -0.4934 0.01140 0.00561 -0.0480 0.7681 0.0100
-6.500 -0.4662 0.01108 0.00524 -0.0479 0.7611 0.0105
-6.250 -0.4390 0.01079 0.00486 -0.0479 0.7541 0.0111
-6.000 -0.4115 0.01052 0.00452 -0.0478 0.7466 0.0116
-5.750 -0.3842 0.01024 0.00417 -0.0477 0.7394 0.0121
-5.500 -0.3567 0.00992 0.00380 -0.0477 0.7319 0.0131
-5.250 -0.3291 0.00969 0.00353 -0.0477 0.7250 0.0141
-5.000 -0.3013 0.00949 0.00329 -0.0477 0.7181 0.0152
-4.500 -0.2456 0.00907 0.00278 -0.0477 0.7047 0.0178
-4.250 -0.2178 0.00889 0.00257 -0.0477 0.6979 0.0195
-4.000 -0.1897 0.00874 0.00238 -0.0477 0.6914 0.0211
-3.750 -0.1617 0.00857 0.00218 -0.0477 0.6844 0.0237
-3.500 -0.1337 0.00841 0.00201 -0.0477 0.6779 0.0267
-3.250 -0.1055 0.00830 0.00185 -0.0478 0.6705 0.0289
-3.000 -0.0774 0.00814 0.00170 -0.0478 0.6636 0.0344
-2.750 -0.0492 0.00803 0.00157 -0.0479 0.6560 0.0397
-2.500 -0.0211 0.00791 0.00145 -0.0479 0.6489 0.0475
-2.250 0.0071 0.00779 0.00134 -0.0480 0.6413 0.0574
-2.000 0.0353 0.00767 0.00125 -0.0481 0.6344 0.0702
-1.750 0.0635 0.00757 0.00116 -0.0482 0.6270 0.0847
-1.500 0.0917 0.00745 0.00108 -0.0482 0.6205 0.1054
-1.250 0.1199 0.00733 0.00102 -0.0483 0.6135 0.1289
-1.000 0.1480 0.00720 0.00097 -0.0484 0.6070 0.1623
-0.750 0.1761 0.00706 0.00092 -0.0486 0.5998 0.2007
-0.500 0.2041 0.00689 0.00088 -0.0487 0.5933 0.2519
-0.250 0.2319 0.00668 0.00086 -0.0488 0.5861 0.3211
0.000 0.2596 0.00645 0.00084 -0.0489 0.5788 0.4011
0.250 0.2870 0.00616 0.00083 -0.0490 0.5706 0.5054
0.500 0.3139 0.00585 0.00084 -0.0490 0.5626 0.6248
0.750 0.3407 0.00562 0.00087 -0.0488 0.5542 0.7220
1.000 0.3677 0.00551 0.00092 -0.0486 0.5464 0.7806
1.250 0.3945 0.00546 0.00097 -0.0483 0.5385 0.8251
1.500 0.4207 0.00541 0.00102 -0.0478 0.5311 0.8662
1.750 0.4467 0.00542 0.00108 -0.0473 0.5232 0.8964
2.000 0.4718 0.00542 0.00114 -0.0465 0.5136 0.9277
2.250 0.4984 0.00544 0.00118 -0.0459 0.5029 0.9663
2.500 0.5349 0.00551 0.00122 -0.0478 0.4908 0.9864
2.750 0.5688 0.00561 0.00128 -0.0492 0.4804 0.9945
3.000 0.6011 0.00570 0.00133 -0.0503 0.4685 1.0000
3.250 0.6278 0.00582 0.00141 -0.0501 0.4563 1.0000
3.500 0.6547 0.00594 0.00151 -0.0500 0.4446 1.0000
3.750 0.6817 0.00608 0.00160 -0.0499 0.4314 1.0000
4.000 0.7079 0.00634 0.00174 -0.0497 0.4009 1.0000
4.250 0.7333 0.00673 0.00192 -0.0495 0.3569 1.0000
4.500 0.7588 0.00712 0.00214 -0.0493 0.3164 1.0000
4.750 0.7845 0.00748 0.00235 -0.0491 0.2830 1.0000
5.000 0.8093 0.00796 0.00263 -0.0488 0.2394 1.0000
5.250 0.8335 0.00852 0.00296 -0.0485 0.1916 1.0000
5.500 0.8571 0.00913 0.00334 -0.0482 0.1433 1.0000
5.750 0.8804 0.00977 0.00375 -0.0477 0.0978 1.0000
6.000 0.9045 0.01029 0.00412 -0.0474 0.0686 1.0000
6.250 0.9290 0.01073 0.00447 -0.0471 0.0497 1.0000
6.500 0.9538 0.01113 0.00481 -0.0468 0.0375 1.0000
6.750 0.9787 0.01149 0.00514 -0.0465 0.0299 1.0000
7.000 1.0035 0.01186 0.00548 -0.0462 0.0246 1.0000
7.250 1.0284 0.01219 0.00581 -0.0459 0.0210 1.0000
7.500 1.0526 0.01259 0.00620 -0.0455 0.0173 1.0000
7.750 1.0771 0.01294 0.00656 -0.0452 0.0153 1.0000
8.000 1.1008 0.01335 0.00697 -0.0447 0.0132 1.0000
8.250 1.1244 0.01376 0.00739 -0.0443 0.0117 1.0000
8.500 1.1478 0.01415 0.00781 -0.0438 0.0106 1.0000
8.750 1.1705 0.01459 0.00828 -0.0432 0.0098 1.0000
9.000 1.1921 0.01511 0.00882 -0.0425 0.0089 1.0000
9.250 1.2137 0.01561 0.00936 -0.0418 0.0084 1.0000
9.500 1.2350 0.01609 0.00989 -0.0411 0.0080 1.0000
9.750 1.2558 0.01658 0.01042 -0.0403 0.0076 1.0000
10.000 1.2756 0.01712 0.01100 -0.0393 0.0073 1.0000
10.250 1.2947 0.01767 0.01159 -0.0383 0.0068 1.0000
10.500 1.3120 0.01830 0.01226 -0.0371 0.0065 1.0000
10.750 1.3267 0.01904 0.01305 -0.0355 0.0061 1.0000
11.000 1.3364 0.01982 0.01390 -0.0331 0.0059 1.0000
11.250 1.3486 0.02046 0.01460 -0.0311 0.0058 1.0000
11.500 1.3583 0.02130 0.01551 -0.0291 0.0057 1.0000
11.750 1.3693 0.02213 0.01641 -0.0274 0.0055 1.0000
12.000 1.3794 0.02308 0.01743 -0.0257 0.0054 1.0000
12.250 1.3880 0.02420 0.01863 -0.0241 0.0053 1.0000
12.500 1.3976 0.02531 0.01982 -0.0228 0.0051 1.0000
12.750 1.4055 0.02660 0.02118 -0.0214 0.0050 1.0000
13.000 1.4138 0.02792 0.02258 -0.0203 0.0048 1.0000
13.250 1.4218 0.02933 0.02406 -0.0193 0.0047 1.0000
13.500 1.4292 0.03084 0.02564 -0.0184 0.0045 1.0000
13.750 1.4359 0.03248 0.02735 -0.0176 0.0044 1.0000
14.000 1.4405 0.03437 0.02931 -0.0168 0.0043 1.0000
14.250 1.4427 0.03658 0.03162 -0.0162 0.0043 1.0000
14.500 1.4434 0.03901 0.03414 -0.0157 0.0040 1.0000
14.750 1.4408 0.04189 0.03714 -0.0154 0.0039 1.0000
15.000 1.4410 0.04459 0.03994 -0.0153 0.0039 1.0000
15.250 1.4432 0.04713 0.04258 -0.0154 0.0038 1.0000
15.500 1.4414 0.05025 0.04582 -0.0157 0.0038 1.0000
15.750 1.4418 0.05322 0.04889 -0.0162 0.0037 1.0000
16.000 1.4424 0.05626 0.05203 -0.0168 0.0037 1.0000
16.250 1.4381 0.06012 0.05601 -0.0178 0.0036 1.0000
16.500 1.4337 0.06413 0.06014 -0.0190 0.0036 1.0000
16.750 1.4286 0.06839 0.06452 -0.0204 0.0036 1.0000
17.000 1.4224 0.07300 0.06924 -0.0222 0.0035 1.0000
17.250 1.4160 0.07781 0.07417 -0.0241 0.0034 1.0000
17.500 1.4047 0.08354 0.08004 -0.0266 0.0035 1.0000
17.750 1.3987 0.08860 0.08521 -0.0290 0.0034 1.0000
18.000 1.3844 0.09528 0.09204 -0.0322 0.0034 1.0000
18.250 1.3729 0.10167 0.09855 -0.0355 0.0034 1.0000
18.500 1.3588 0.10876 0.10577 -0.0392 0.0034 1.0000
18.750 1.3441 0.11618 0.11333 -0.0433 0.0033 1.0000
19.000 1.3301 0.12359 0.12087 -0.0474 0.0033 1.0000
19.250 1.3132 0.13186 0.12927 -0.0522 0.0033 1.0000
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Polar data table (+)
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