FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 50,000 Max Cl/Cd: 10.7 at α=-1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63143-il-50000.txt Download as CSV file: xf-fx63143-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-143 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3577 0.12694 0.12027 -0.0265 1.0000 0.2257
-10.500 -0.3368 0.12188 0.11520 -0.0256 1.0000 0.2348
-10.250 -0.3667 0.12210 0.11559 -0.0277 1.0000 0.2434
-10.000 -0.3330 0.11614 0.10962 -0.0259 1.0000 0.2557
-9.750 -0.3289 0.11278 0.10634 -0.0259 1.0000 0.2644
-9.500 -0.3409 0.11092 0.10462 -0.0263 1.0000 0.2762
-9.250 -0.3435 0.10872 0.10251 -0.0259 1.0000 0.2902
-9.000 -0.3240 0.10454 0.09837 -0.0247 1.0000 0.3039
-8.750 -0.3153 0.10120 0.09510 -0.0237 1.0000 0.3181
-8.500 -0.3099 0.09798 0.09198 -0.0230 1.0000 0.3302
-8.250 -0.3090 0.09522 0.08933 -0.0220 1.0000 0.3438
-8.000 -0.3082 0.09252 0.08675 -0.0208 1.0000 0.3589
-5.750 -0.5570 0.06097 0.05518 -0.0277 0.9828 0.1402
-5.500 -0.5329 0.05442 0.04752 -0.0305 0.9727 0.1100
-5.250 -0.5010 0.05011 0.04247 -0.0327 0.9632 0.0987
-5.000 -0.4677 0.04642 0.03776 -0.0343 0.9535 0.0910
-4.750 -0.4367 0.04358 0.03462 -0.0355 0.9442 0.0894
-4.500 -0.3963 0.04088 0.03140 -0.0378 0.9361 0.0887
-4.250 -0.3671 0.03906 0.02911 -0.0379 0.9272 0.0898
-4.000 -0.3260 0.03711 0.02699 -0.0400 0.9198 0.0954
-3.750 -0.2951 0.03584 0.02559 -0.0404 0.9115 0.1058
-3.500 -0.2552 0.03452 0.02422 -0.0418 0.9037 0.1240
-3.250 -0.2234 0.03362 0.02335 -0.0424 0.8959 0.1448
-3.000 -0.1990 0.03258 0.02250 -0.0423 0.8880 0.1717
-2.750 0.2033 0.03041 0.02213 -0.0912 0.9008 1.0000
-2.500 0.2138 0.03068 0.02222 -0.0906 0.8887 1.0000
-2.250 0.2398 0.03069 0.02202 -0.0923 0.8792 1.0000
-2.000 0.2628 0.03079 0.02192 -0.0932 0.8689 1.0000
-1.750 0.2727 0.03127 0.02223 -0.0918 0.8576 1.0000
-1.500 0.3105 0.03113 0.02186 -0.0946 0.8492 1.0000
-1.250 0.3025 0.03214 0.02280 -0.0902 0.8377 1.0000
-1.000 0.3430 0.03206 0.02252 -0.0931 0.8308 1.0000
-0.750 0.3148 0.03368 0.02412 -0.0858 0.8201 1.0000
-0.500 0.3454 0.03400 0.02428 -0.0872 0.8141 1.0000
-0.250 0.3059 0.03587 0.02616 -0.0783 0.8050 1.0000
0.000 0.3283 0.03645 0.02659 -0.0784 0.7983 1.0000
0.250 0.2966 0.03803 0.02814 -0.0704 0.7908 1.0000
0.500 0.2848 0.03921 0.02926 -0.0655 0.7842 1.0000
0.750 0.3215 0.03981 0.02973 -0.0676 0.7790 1.0000
1.000 0.2714 0.04161 0.03152 -0.0575 0.7746 1.0000
1.250 0.2595 0.04276 0.03260 -0.0528 0.7686 1.0000
1.500 0.2960 0.04344 0.03316 -0.0545 0.7607 1.0000
1.750 0.2661 0.04471 0.03439 -0.0473 0.7541 1.0000
2.000 0.2830 0.04562 0.03522 -0.0464 0.7472 1.0000
2.250 0.2876 0.04682 0.03635 -0.0441 0.7425 1.0000
2.500 0.2713 0.04817 0.03766 -0.0394 0.7402 1.0000
2.750 0.2634 0.04954 0.03897 -0.0360 0.7391 1.0000
3.000 0.2600 0.05097 0.04035 -0.0334 0.7394 1.0000
3.250 0.2598 0.05245 0.04179 -0.0314 0.7401 1.0000
3.500 0.2629 0.05401 0.04330 -0.0299 0.7411 1.0000
3.750 0.2731 0.05579 0.04504 -0.0296 0.7433 1.0000
4.000 0.1261 0.05684 0.04625 -0.0152 0.9026 1.0000
4.250 0.1498 0.05850 0.04786 -0.0166 0.8862 1.0000
4.500 0.1758 0.06041 0.04971 -0.0182 0.8687 1.0000
4.750 0.1958 0.06196 0.05123 -0.0189 0.8531 1.0000
5.000 0.2142 0.06362 0.05286 -0.0194 0.8397 1.0000
5.250 0.2449 0.06648 0.05569 -0.0219 0.8296 1.0000
5.500 0.2633 0.06796 0.05717 -0.0223 0.8153 1.0000
5.750 0.2726 0.06911 0.05831 -0.0216 0.8030 1.0000
6.000 0.3013 0.07212 0.06132 -0.0238 0.7948 1.0000
6.250 0.3177 0.07361 0.06283 -0.0240 0.7807 1.0000
6.500 0.3296 0.07502 0.06425 -0.0236 0.7662 1.0000
6.750 0.3448 0.07684 0.06609 -0.0238 0.7523 1.0000
7.000 0.3663 0.07933 0.06863 -0.0248 0.7411 1.0000
7.250 0.3995 0.08256 0.07191 -0.0271 0.7276 1.0000
7.500 0.4037 0.08343 0.07281 -0.0259 0.7132 1.0000
7.750 0.4116 0.08510 0.07452 -0.0255 0.7010 1.0000
8.000 0.4382 0.08833 0.07784 -0.0272 0.6917 1.0000
8.250 0.4525 0.09016 0.07975 -0.0273 0.6782 1.0000
8.500 0.4560 0.09174 0.08137 -0.0266 0.6662 1.0000
8.750 0.4811 0.09514 0.08485 -0.0282 0.6573 1.0000
9.000 0.4973 0.09729 0.08711 -0.0286 0.6434 1.0000
9.250 0.4992 0.09882 0.08871 -0.0279 0.6304 1.0000
9.500 0.5111 0.10132 0.09130 -0.0282 0.6188 1.0000
9.750 0.5424 0.10523 0.09535 -0.0301 0.6071 1.0000
10.000 0.5545 0.10726 0.09748 -0.0301 0.5921 1.0000
10.250 0.5556 0.10886 0.09916 -0.0296 0.5782 1.0000
10.500 0.5644 0.11116 0.10156 -0.0297 0.5641 1.0000
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