FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 73-K-170/22 (fx73k170-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.09 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx73k170-il-1000000.txt Download as CSV file: xf-fx73k170-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-K-170/22
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.3336 0.04876 0.04548 -0.1420 0.7852 0.0092
-12.000 -0.3333 0.04450 0.04101 -0.1474 0.7833 0.0090
-11.750 -0.3501 0.03924 0.03556 -0.1516 0.7817 0.0090
-11.500 -0.3536 0.03540 0.03161 -0.1538 0.7798 0.0086
-11.250 -0.3425 0.03414 0.03019 -0.1561 0.7778 0.0090
-11.000 -0.3370 0.03186 0.02775 -0.1578 0.7757 0.0089
-10.750 -0.3461 0.02728 0.02290 -0.1586 0.7735 0.0087
-10.250 -0.3302 0.02440 0.01967 -0.1577 0.7691 0.0087
-10.000 -0.3199 0.02387 0.01899 -0.1563 0.7673 0.0089
-9.750 -0.3113 0.02204 0.01698 -0.1547 0.7656 0.0089
-9.500 -0.2975 0.02066 0.01546 -0.1535 0.7638 0.0089
-9.250 -0.2841 0.01885 0.01346 -0.1522 0.7619 0.0090
-9.000 -0.2707 0.01725 0.01178 -0.1508 0.7600 0.0096
-8.750 -0.2526 0.01637 0.01080 -0.1498 0.7582 0.0095
-8.500 -0.2331 0.01574 0.01011 -0.1489 0.7563 0.0096
-8.250 -0.2119 0.01524 0.00954 -0.1483 0.7541 0.0100
-8.000 -0.1911 0.01473 0.00898 -0.1476 0.7521 0.0103
-7.750 -0.1717 0.01413 0.00834 -0.1466 0.7505 0.0103
-7.500 -0.1497 0.01373 0.00791 -0.1459 0.7486 0.0110
-7.250 -0.1288 0.01321 0.00734 -0.1451 0.7466 0.0111
-7.000 -0.1060 0.01282 0.00690 -0.1445 0.7446 0.0114
-6.750 -0.0830 0.01245 0.00648 -0.1440 0.7426 0.0116
-6.500 -0.0612 0.01195 0.00592 -0.1433 0.7406 0.0119
-6.250 -0.0391 0.01145 0.00533 -0.1427 0.7380 0.0125
-6.000 -0.0159 0.01109 0.00498 -0.1422 0.7363 0.0134
-5.750 0.0084 0.01081 0.00468 -0.1418 0.7343 0.0142
-5.500 0.0334 0.01055 0.00440 -0.1415 0.7322 0.0149
-5.250 0.0573 0.01018 0.00400 -0.1410 0.7299 0.0174
-5.000 0.0830 0.00996 0.00374 -0.1408 0.7278 0.0193
-4.750 0.1075 0.00962 0.00343 -0.1404 0.7256 0.0289
-4.500 0.1327 0.00934 0.00321 -0.1403 0.7230 0.0517
-4.250 0.1564 0.00901 0.00302 -0.1398 0.7211 0.0832
-4.000 0.1795 0.00861 0.00281 -0.1393 0.7188 0.1353
-3.750 0.2007 0.00806 0.00258 -0.1385 0.7163 0.2263
-3.500 0.2217 0.00752 0.00236 -0.1377 0.7139 0.3247
-3.250 0.2427 0.00702 0.00216 -0.1367 0.7115 0.4285
-3.000 0.2660 0.00675 0.00211 -0.1361 0.7089 0.5112
-2.750 0.2920 0.00671 0.00214 -0.1358 0.7066 0.5456
-2.500 0.3188 0.00670 0.00213 -0.1357 0.7041 0.5612
-2.250 0.3460 0.00670 0.00212 -0.1357 0.7013 0.5724
-2.000 0.3735 0.00673 0.00211 -0.1356 0.6985 0.5836
-1.750 0.4008 0.00677 0.00214 -0.1356 0.6960 0.5940
-1.500 0.4289 0.00685 0.00215 -0.1358 0.6933 0.6012
-1.250 0.4556 0.00685 0.00217 -0.1356 0.6909 0.6062
-1.000 0.4827 0.00688 0.00219 -0.1356 0.6880 0.6114
-0.750 0.5099 0.00692 0.00219 -0.1355 0.6852 0.6156
-0.500 0.5371 0.00691 0.00217 -0.1355 0.6825 0.6193
-0.250 0.5647 0.00696 0.00219 -0.1356 0.6797 0.6228
0.000 0.5916 0.00700 0.00223 -0.1356 0.6770 0.6263
0.250 0.6183 0.00702 0.00225 -0.1355 0.6741 0.6295
0.500 0.6452 0.00706 0.00226 -0.1354 0.6711 0.6319
0.750 0.6719 0.00705 0.00225 -0.1354 0.6682 0.6351
1.000 0.6990 0.00710 0.00228 -0.1354 0.6649 0.6376
1.250 0.7253 0.00713 0.00232 -0.1352 0.6620 0.6403
1.500 0.7514 0.00715 0.00236 -0.1350 0.6588 0.6429
1.750 0.7777 0.00719 0.00238 -0.1349 0.6556 0.6451
2.000 0.8040 0.00725 0.00242 -0.1348 0.6524 0.6472
2.250 0.8305 0.00730 0.00245 -0.1347 0.6489 0.6494
2.500 0.8558 0.00730 0.00250 -0.1343 0.6457 0.6518
2.750 0.8814 0.00733 0.00256 -0.1341 0.6424 0.6539
3.000 0.9069 0.00738 0.00261 -0.1338 0.6389 0.6560
3.250 0.9329 0.00748 0.00267 -0.1336 0.6351 0.6582
3.500 0.9577 0.00752 0.00274 -0.1332 0.6320 0.6604
3.750 0.9822 0.00756 0.00282 -0.1327 0.6282 0.6625
4.000 1.0067 0.00762 0.00288 -0.1322 0.6243 0.6644
4.250 1.0315 0.00770 0.00295 -0.1319 0.6203 0.6668
4.500 1.0554 0.00774 0.00305 -0.1313 0.6169 0.6691
4.750 1.0783 0.00778 0.00314 -0.1305 0.6122 0.6713
5.000 1.1011 0.00787 0.00322 -0.1296 0.6077 0.6738
5.250 1.1229 0.00795 0.00333 -0.1286 0.6023 0.6761
5.500 1.1443 0.00802 0.00343 -0.1275 0.5969 0.6782
5.750 1.1639 0.00812 0.00352 -0.1260 0.5918 0.6808
6.000 1.1823 0.00817 0.00363 -0.1243 0.5858 0.6834
6.250 1.1999 0.00827 0.00376 -0.1224 0.5789 0.6861
6.500 1.2187 0.00842 0.00393 -0.1208 0.5730 0.6886
6.750 1.2358 0.00858 0.00410 -0.1189 0.5634 0.6912
7.000 1.2520 0.00878 0.00432 -0.1169 0.5528 0.6938
7.250 1.2654 0.00907 0.00459 -0.1144 0.5383 0.6966
7.500 1.2786 0.00943 0.00493 -0.1120 0.5213 0.7000
7.750 1.2926 0.00986 0.00534 -0.1099 0.5054 0.7033
8.000 1.3024 0.01053 0.00595 -0.1074 0.4845 0.7066
8.250 1.3158 0.01123 0.00660 -0.1058 0.4651 0.7099
8.750 1.3373 0.01356 0.00876 -0.1032 0.4093 0.7176
9.000 1.3488 0.01483 0.00995 -0.1022 0.3824 0.7220
9.250 1.3571 0.01628 0.01129 -0.1008 0.3539 0.7263
9.500 1.3587 0.01836 0.01317 -0.0991 0.3103 0.7312
9.750 1.3660 0.02001 0.01471 -0.0980 0.2811 0.7364
10.000 1.3584 0.02257 0.01699 -0.0952 0.2313 0.7417
10.250 1.3665 0.02434 0.01866 -0.0944 0.2036 0.7480
10.500 1.3639 0.02672 0.02083 -0.0924 0.1643 0.7555
10.750 1.3690 0.02864 0.02265 -0.0912 0.1378 0.7642
11.000 1.3743 0.03058 0.02450 -0.0901 0.1154 0.7755
11.250 1.3770 0.03283 0.02664 -0.0889 0.0881 0.7917
11.500 1.3863 0.03474 0.02856 -0.0886 0.0697 0.8186
11.750 1.4112 0.03694 0.03096 -0.0919 0.0513 0.9360
12.000 1.4226 0.03891 0.03288 -0.0915 0.0415 1.0000
12.250 1.4288 0.04070 0.03464 -0.0902 0.0351 1.0000
12.500 1.4373 0.04231 0.03626 -0.0892 0.0310 1.0000
12.750 1.4447 0.04403 0.03799 -0.0881 0.0272 1.0000
13.000 1.4534 0.04567 0.03965 -0.0872 0.0251 1.0000
13.250 1.4599 0.04753 0.04152 -0.0861 0.0218 1.0000
13.500 1.4691 0.04919 0.04322 -0.0853 0.0205 1.0000
13.750 1.4761 0.05102 0.04507 -0.0844 0.0186 1.0000
14.000 1.4825 0.05297 0.04705 -0.0836 0.0168 1.0000
14.250 1.4905 0.05475 0.04887 -0.0828 0.0152 1.0000
14.500 1.4949 0.05695 0.05109 -0.0819 0.0135 1.0000
14.750 1.5022 0.05887 0.05306 -0.0812 0.0122 1.0000
15.000 1.5051 0.06126 0.05547 -0.0804 0.0105 1.0000
15.250 1.5101 0.06346 0.05772 -0.0797 0.0099 1.0000
15.500 1.5148 0.06572 0.06004 -0.0791 0.0090 1.0000
15.750 1.5193 0.06800 0.06237 -0.0785 0.0084 1.0000
16.000 1.5182 0.07098 0.06540 -0.0777 0.0075 1.0000
16.250 1.5239 0.07321 0.06770 -0.0773 0.0070 1.0000
16.500 1.5269 0.07578 0.07033 -0.0769 0.0067 1.0000
16.750 1.5289 0.07846 0.07308 -0.0765 0.0064 1.0000
17.000 1.5295 0.08135 0.07603 -0.0762 0.0060 1.0000
17.250 1.5272 0.08465 0.07941 -0.0758 0.0057 1.0000
17.500 1.5231 0.08825 0.08311 -0.0756 0.0054 1.0000
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