FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 68-H-120 (fx68h120-il) Reynolds number: 100,000 Max Cl/Cd: 40.23 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx68h120-il-100000.txt Download as CSV file: xf-fx68h120-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 68-H-120
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4791 0.07575 0.07156 -0.0454 1.0000 0.0556
-9.250 -0.4889 0.06978 0.06564 -0.0498 1.0000 0.0544
-9.000 -0.5093 0.06453 0.06040 -0.0523 1.0000 0.0531
-8.750 -0.5420 0.06177 0.05765 -0.0490 1.0000 0.0525
-8.500 -0.5727 0.05918 0.05501 -0.0447 1.0000 0.0516
-8.250 -0.6021 0.05596 0.05168 -0.0405 1.0000 0.0507
-8.000 -0.6325 0.05154 0.04699 -0.0362 1.0000 0.0494
-7.750 -0.6678 0.04528 0.04001 -0.0311 1.0000 0.0470
-7.500 -0.6769 0.04143 0.03560 -0.0270 1.0000 0.0461
-7.250 -0.6765 0.03834 0.03213 -0.0238 1.0000 0.0465
-7.000 -0.6710 0.03576 0.02921 -0.0209 1.0000 0.0471
-6.750 -0.6610 0.03408 0.02735 -0.0186 1.0000 0.0494
-6.500 -0.6496 0.03227 0.02523 -0.0162 1.0000 0.0523
-6.250 -0.6363 0.03005 0.02256 -0.0138 1.0000 0.0539
-6.000 -0.6198 0.02810 0.02018 -0.0116 1.0000 0.0557
-5.750 -0.6027 0.02600 0.01794 -0.0098 1.0000 0.0590
-5.500 -0.5849 0.02477 0.01664 -0.0080 1.0000 0.0645
-5.250 -0.5674 0.02364 0.01548 -0.0062 1.0000 0.0753
-5.000 -0.5494 0.02278 0.01459 -0.0044 1.0000 0.0957
-4.750 -0.5336 0.02279 0.01454 -0.0023 1.0000 0.1353
-4.500 -0.5182 0.02295 0.01472 -0.0005 1.0000 0.1655
-4.250 -0.5014 0.02302 0.01479 0.0010 1.0000 0.1875
-4.000 -0.4837 0.02292 0.01454 0.0024 1.0000 0.2071
-3.750 -0.4647 0.02263 0.01425 0.0036 1.0000 0.2230
-3.500 -0.4430 0.02231 0.01385 0.0043 0.9994 0.2369
-3.250 -0.4007 0.02215 0.01365 0.0010 0.9917 0.2532
-3.000 -0.3559 0.02203 0.01345 -0.0026 0.9838 0.2687
-2.750 -0.3160 0.02182 0.01321 -0.0053 0.9747 0.2838
-2.500 -0.2750 0.02165 0.01305 -0.0080 0.9652 0.3006
-2.250 -0.2312 0.02153 0.01294 -0.0113 0.9555 0.3221
-2.000 -0.1873 0.02128 0.01287 -0.0144 0.9457 0.3512
-1.750 -0.1522 0.02085 0.01277 -0.0159 0.9347 0.3959
-1.500 0.0585 0.01940 0.01334 -0.0481 0.9399 0.9916
-1.250 0.1416 0.01939 0.01303 -0.0586 0.9325 1.0000
-1.000 0.1914 0.01931 0.01279 -0.0627 0.9207 1.0000
-0.750 0.2444 0.01911 0.01245 -0.0672 0.9089 1.0000
-0.500 0.2896 0.01885 0.01209 -0.0699 0.8960 1.0000
-0.250 0.3275 0.01852 0.01168 -0.0710 0.8818 1.0000
0.000 0.3582 0.01815 0.01124 -0.0705 0.8666 1.0000
0.250 0.3837 0.01775 0.01078 -0.0689 0.8509 1.0000
0.500 0.4061 0.01732 0.01029 -0.0666 0.8350 1.0000
0.750 0.4262 0.01685 0.00977 -0.0638 0.8186 1.0000
1.000 0.4429 0.01648 0.00937 -0.0606 0.7981 1.0000
1.250 0.4624 0.01593 0.00877 -0.0576 0.7790 1.0000
1.500 0.4808 0.01547 0.00826 -0.0547 0.7553 1.0000
1.750 0.5001 0.01498 0.00772 -0.0518 0.7269 1.0000
2.000 0.5199 0.01454 0.00717 -0.0491 0.6905 1.0000
2.250 0.5398 0.01424 0.00667 -0.0464 0.6415 1.0000
2.500 0.5596 0.01421 0.00625 -0.0439 0.5862 1.0000
2.750 0.5792 0.01456 0.00616 -0.0418 0.5376 1.0000
3.000 0.5993 0.01510 0.00635 -0.0401 0.4976 1.0000
3.250 0.6199 0.01569 0.00662 -0.0387 0.4657 1.0000
3.500 0.6409 0.01626 0.00696 -0.0374 0.4376 1.0000
3.750 0.6620 0.01682 0.00737 -0.0362 0.4125 1.0000
4.000 0.6835 0.01740 0.00776 -0.0351 0.3917 1.0000
4.250 0.7052 0.01796 0.00822 -0.0340 0.3729 1.0000
4.500 0.7273 0.01855 0.00871 -0.0331 0.3571 1.0000
4.750 0.7497 0.01916 0.00925 -0.0321 0.3432 1.0000
5.000 0.7721 0.01977 0.00979 -0.0312 0.3309 1.0000
5.250 0.7949 0.02040 0.01033 -0.0304 0.3201 1.0000
5.500 0.8177 0.02100 0.01090 -0.0295 0.3101 1.0000
5.750 0.8401 0.02167 0.01163 -0.0287 0.3011 1.0000
6.000 0.8646 0.02240 0.01227 -0.0281 0.2944 1.0000
6.250 0.8864 0.02312 0.01317 -0.0272 0.2872 1.0000
6.500 0.9105 0.02387 0.01388 -0.0266 0.2815 1.0000
6.750 0.9327 0.02472 0.01488 -0.0258 0.2759 1.0000
7.000 0.9550 0.02549 0.01575 -0.0249 0.2702 1.0000
7.250 0.9800 0.02637 0.01660 -0.0246 0.2658 1.0000
7.500 0.9983 0.02713 0.01766 -0.0232 0.2594 1.0000
7.750 1.0174 0.02723 0.01770 -0.0219 0.2482 1.0000
8.000 1.0373 0.02728 0.01760 -0.0207 0.2373 1.0000
8.250 1.0510 0.02725 0.01774 -0.0186 0.2259 1.0000
8.500 1.0639 0.02724 0.01783 -0.0165 0.2141 1.0000
8.750 1.0785 0.02739 0.01808 -0.0146 0.2048 1.0000
9.000 1.0878 0.02726 0.01805 -0.0119 0.1925 1.0000
9.250 1.0976 0.02733 0.01815 -0.0093 0.1818 1.0000
9.500 1.1015 0.02738 0.01837 -0.0060 0.1657 1.0000
9.750 1.1105 0.02768 0.01880 -0.0034 0.1498 1.0000
10.000 1.1195 0.02815 0.01931 -0.0008 0.1301 1.0000
10.250 1.1308 0.02887 0.02006 0.0013 0.1043 1.0000
10.500 1.1194 0.03132 0.02190 0.0050 0.0450 1.0000
10.750 1.1172 0.03344 0.02402 0.0077 0.0392 1.0000
11.000 1.1175 0.03539 0.02608 0.0100 0.0363 1.0000
11.250 1.1186 0.03730 0.02819 0.0120 0.0351 1.0000
11.500 1.1177 0.03942 0.03052 0.0138 0.0342 1.0000
11.750 1.1143 0.04184 0.03315 0.0152 0.0336 1.0000
12.000 1.1066 0.04482 0.03634 0.0164 0.0329 1.0000
12.250 1.0980 0.04809 0.03982 0.0169 0.0326 1.0000
12.500 1.0852 0.05215 0.04414 0.0167 0.0323 1.0000
12.750 1.0695 0.05703 0.04922 0.0154 0.0320 1.0000
13.000 1.0516 0.06289 0.05529 0.0132 0.0320 1.0000
13.250 1.0352 0.06912 0.06170 0.0102 0.0324 1.0000
13.500 1.0166 0.07610 0.06886 0.0068 0.0327 1.0000
13.750 0.9956 0.08364 0.07653 0.0033 0.0326 1.0000
14.000 0.9805 0.09013 0.08314 0.0004 0.0327 1.0000
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Polar data table (+)
Polar graphs
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