FX 67-K-170/17 AIRFOIL (fx67k170-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 67-K-170/17 AIRFOIL (fx67k170-il) Reynolds number: 100,000 Max Cl/Cd: 19.85 at α=12.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx67k170-il-100000-n5.txt Download as CSV file: xf-fx67k170-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 67-K-170/17 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0869 0.11509 0.10938 -0.1045 0.7945 0.0527
-11.500 -0.0967 0.11211 0.10648 -0.1085 0.7922 0.0540
-11.250 -0.1011 0.10869 0.10310 -0.1114 0.7899 0.0543
-11.000 -0.0914 0.10419 0.09861 -0.1111 0.7883 0.0553
-10.750 -0.0832 0.10096 0.09537 -0.1114 0.7866 0.0559
-10.500 -0.0832 0.09322 0.08757 -0.1137 0.7853 0.0315
-10.250 -0.0790 0.09026 0.08461 -0.1143 0.7838 0.0306
-10.000 -0.0784 0.08666 0.08107 -0.1160 0.7813 0.0296
-9.750 -0.0814 0.08247 0.07694 -0.1182 0.7786 0.0287
-9.500 -0.0880 0.07755 0.07206 -0.1212 0.7760 0.0277
-9.000 -0.1506 0.06289 0.05710 -0.1297 0.7707 0.0245
-8.750 -0.1656 0.06072 0.05488 -0.1282 0.7677 0.0244
-8.500 -0.1763 0.05860 0.05267 -0.1266 0.7642 0.0242
-8.250 -0.1850 0.05613 0.05004 -0.1248 0.7611 0.0241
-8.000 -0.1902 0.05358 0.04727 -0.1228 0.7585 0.0240
-7.750 -0.1916 0.05100 0.04442 -0.1208 0.7565 0.0239
-7.500 -0.1919 0.04872 0.04186 -0.1187 0.7535 0.0238
-7.250 -0.1912 0.04679 0.03967 -0.1165 0.7496 0.0238
-7.000 -0.1860 0.04464 0.03716 -0.1143 0.7466 0.0239
-6.750 -0.1765 0.04244 0.03454 -0.1123 0.7443 0.0241
-6.500 -0.1637 0.04029 0.03192 -0.1105 0.7425 0.0249
-6.250 -0.1462 0.03872 0.03022 -0.1098 0.7411 0.0263
-6.000 -0.1417 0.03858 0.03002 -0.1074 0.7353 0.0274
-5.750 -0.1267 0.03750 0.02866 -0.1059 0.7325 0.0288
-5.500 -0.1069 0.03604 0.02688 -0.1047 0.7304 0.0296
-5.250 -0.0836 0.03461 0.02514 -0.1038 0.7289 0.0308
-5.000 -0.0586 0.03350 0.02372 -0.1031 0.7275 0.0323
-4.750 -0.0564 0.03348 0.02380 -0.1002 0.7217 0.0343
-4.500 -0.0419 0.03318 0.02347 -0.0986 0.7184 0.0370
-4.250 -0.0214 0.03256 0.02273 -0.0975 0.7164 0.0397
-4.000 0.0010 0.03185 0.02191 -0.0967 0.7148 0.0435
-3.750 0.0238 0.03107 0.02111 -0.0960 0.7135 0.0469
-3.500 0.0155 0.03203 0.02208 -0.0915 0.7061 0.0483
-3.250 0.0311 0.03198 0.02192 -0.0900 0.7033 0.0530
-3.000 0.0517 0.03158 0.02147 -0.0890 0.7015 0.0580
-2.750 0.0762 0.03119 0.02095 -0.0886 0.7001 0.0655
-2.500 0.0718 0.03201 0.02178 -0.0845 0.6937 0.0710
-2.250 0.0795 0.03216 0.02203 -0.0820 0.6898 0.0935
-2.000 0.0934 0.03094 0.02191 -0.0807 0.6878 0.3277
-1.750 0.1042 0.02997 0.02223 -0.0772 0.6863 0.6234
-1.500 0.1155 0.03026 0.02283 -0.0722 0.6850 0.7735
-1.250 0.0947 0.03191 0.02453 -0.0656 0.6764 0.8018
-1.000 0.0961 0.03238 0.02505 -0.0592 0.6740 0.8593
-0.750 0.1078 0.03253 0.02514 -0.0548 0.6723 0.8971
-0.500 0.1358 0.03265 0.02511 -0.0540 0.6712 0.9221
-0.250 0.1385 0.03397 0.02640 -0.0520 0.6641 0.9387
0.000 0.1714 0.03450 0.02676 -0.0540 0.6618 0.9487
0.250 0.2071 0.03489 0.02699 -0.0563 0.6601 0.9572
0.500 0.2467 0.03518 0.02711 -0.0592 0.6587 0.9641
0.750 0.2862 0.03539 0.02719 -0.0620 0.6575 0.9705
1.000 0.3273 0.03559 0.02725 -0.0651 0.6566 0.9757
1.250 0.3346 0.03759 0.02925 -0.0657 0.6484 0.9886
1.500 0.3648 0.03798 0.02954 -0.0672 0.6463 1.0000
1.750 0.3795 0.03794 0.02941 -0.0654 0.6443 1.0000
2.000 0.4000 0.03795 0.02932 -0.0646 0.6429 1.0000
2.250 0.3815 0.03959 0.03095 -0.0599 0.6341 1.0000
2.500 0.4042 0.03989 0.03116 -0.0598 0.6318 1.0000
2.750 0.4301 0.04012 0.03132 -0.0601 0.6301 1.0000
3.000 0.4586 0.04026 0.03139 -0.0606 0.6289 1.0000
3.250 0.4514 0.04208 0.03320 -0.0579 0.6199 1.0000
3.500 0.4765 0.04243 0.03350 -0.0581 0.6176 1.0000
3.750 0.5046 0.04262 0.03364 -0.0586 0.6159 1.0000
4.000 0.5347 0.04272 0.03371 -0.0592 0.6146 1.0000
4.250 0.5289 0.04465 0.03564 -0.0568 0.6051 1.0000
4.500 0.5556 0.04490 0.03587 -0.0572 0.6029 1.0000
4.750 0.5850 0.04501 0.03596 -0.0577 0.6013 1.0000
5.250 0.6092 0.04708 0.03806 -0.0560 0.5896 1.0000
5.500 0.6381 0.04717 0.03815 -0.0565 0.5878 1.0000
5.750 0.6687 0.04717 0.03816 -0.0571 0.5864 1.0000
6.000 0.6642 0.04921 0.04025 -0.0549 0.5760 1.0000
6.250 0.6924 0.04930 0.04037 -0.0553 0.5739 1.0000
6.500 0.7231 0.04921 0.04031 -0.0558 0.5724 1.0000
6.750 0.7201 0.05124 0.04238 -0.0539 0.5619 1.0000
7.000 0.7490 0.05121 0.04242 -0.0543 0.5597 1.0000
7.250 0.7793 0.05106 0.04233 -0.0547 0.5581 1.0000
7.500 0.7776 0.05305 0.04438 -0.0530 0.5472 1.0000
7.750 0.8067 0.05292 0.04434 -0.0533 0.5450 1.0000
8.250 0.8361 0.05465 0.04622 -0.0521 0.5320 1.0000
8.500 0.8669 0.05428 0.04593 -0.0524 0.5300 1.0000
8.750 0.8675 0.05621 0.04795 -0.0510 0.5189 1.0000
9.000 0.8976 0.05580 0.04766 -0.0512 0.5165 1.0000
9.500 0.9345 0.05642 0.04849 -0.0501 0.5024 1.0000
10.000 0.9781 0.05595 0.04826 -0.0490 0.4874 1.0000
10.500 0.9978 0.05814 0.05067 -0.0471 0.4653 1.0000
10.750 1.0246 0.05752 0.05019 -0.0468 0.4598 1.0000
11.250 1.0523 0.05911 0.05206 -0.0455 0.4379 1.0000
11.500 1.0779 0.05853 0.05160 -0.0450 0.4277 1.0000
11.750 1.0999 0.05836 0.05154 -0.0445 0.4147 1.0000
12.000 1.1140 0.05913 0.05240 -0.0438 0.3967 1.0000
12.250 1.1410 0.05818 0.05143 -0.0431 0.3714 1.0000
12.500 1.1592 0.05839 0.05158 -0.0424 0.3437 1.0000
12.750 1.1725 0.05921 0.05233 -0.0415 0.3149 1.0000
13.000 1.1803 0.06066 0.05366 -0.0405 0.2835 1.0000
13.250 1.1829 0.06281 0.05568 -0.0395 0.2515 1.0000
13.500 1.1823 0.06541 0.05813 -0.0386 0.2194 1.0000
13.750 1.1787 0.06846 0.06102 -0.0377 0.1872 1.0000
14.000 1.1739 0.07176 0.06419 -0.0371 0.1562 1.0000
14.250 1.1688 0.07523 0.06750 -0.0365 0.1273 1.0000
14.500 1.1642 0.07873 0.07087 -0.0361 0.1048 1.0000
14.750 1.1622 0.08199 0.07407 -0.0359 0.0899 1.0000
15.250 1.1612 0.08836 0.08042 -0.0357 0.0700 1.0000
15.500 1.1619 0.09147 0.08355 -0.0359 0.0617 1.0000
15.750 1.1609 0.09485 0.08691 -0.0362 0.0543 1.0000
16.000 1.1611 0.09812 0.09022 -0.0366 0.0467 1.0000
16.250 1.1626 0.10127 0.09346 -0.0371 0.0413 1.0000
16.500 1.1615 0.10482 0.09706 -0.0377 0.0370 1.0000
16.750 1.1618 0.10821 0.10060 -0.0383 0.0333 1.0000
17.000 1.1616 0.11171 0.10422 -0.0390 0.0296 1.0000
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