WORTMANN FX 79-K-144/17 AIRFOIL (fx79k144-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 79-K-144/17 AIRFOIL (fx79k144-il) Reynolds number: 100,000 Max Cl/Cd: 44.33 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx79k144-il-100000.txt Download as CSV file: xf-fx79k144-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 79-K-144/17 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4352 0.12381 0.11946 -0.0378 1.0000 0.1073
-10.500 -0.4659 0.12193 0.11768 -0.0394 1.0000 0.1095
-10.250 -0.4983 0.11823 0.11408 -0.0458 0.9977 0.1103
-10.000 -0.4506 0.11373 0.10948 -0.0394 0.9975 0.1143
-9.750 -0.4452 0.11044 0.10620 -0.0402 0.9959 0.1187
-9.500 -0.4639 0.10642 0.10223 -0.0450 0.9936 0.1236
-9.250 -0.5074 0.10194 0.09784 -0.0518 0.9898 0.1248
-9.000 -0.4597 0.09867 0.09452 -0.0460 0.9895 0.1308
-8.750 -0.4671 0.09497 0.09085 -0.0484 0.9869 0.1363
-8.500 -0.4966 0.09068 0.08660 -0.0519 0.9841 0.1380
-8.250 -0.5303 0.08814 0.08408 -0.0505 0.9810 0.1385
-8.000 -0.5855 0.08576 0.08145 -0.0512 0.9760 0.1403
-7.750 -0.5356 0.08099 0.07691 -0.0500 0.9754 0.1480
-7.500 -0.5609 0.07780 0.07356 -0.0505 0.9719 0.1541
-7.250 -0.5706 0.07429 0.07004 -0.0484 0.9695 0.1590
-7.000 -0.5697 0.07206 0.06772 -0.0470 0.9665 0.1686
-6.750 -0.6021 0.05347 0.04742 -0.0473 0.9640 0.0834
-6.500 -0.5842 0.04912 0.04265 -0.0471 0.9618 0.0791
-6.250 -0.5646 0.04502 0.03802 -0.0472 0.9595 0.0785
-6.000 -0.5510 0.04262 0.03500 -0.0454 0.9564 0.0807
-5.750 -0.5299 0.03962 0.03164 -0.0455 0.9533 0.0842
-5.500 -0.4998 0.03719 0.02876 -0.0464 0.9500 0.0848
-5.250 -0.4613 0.03561 0.02694 -0.0490 0.9465 0.0886
-5.000 -0.4394 0.03430 0.02533 -0.0482 0.9424 0.0904
-4.750 -0.4121 0.03305 0.02378 -0.0482 0.9384 0.0920
-4.500 -0.3783 0.03202 0.02247 -0.0493 0.9348 0.0946
-4.250 -0.3377 0.03085 0.02129 -0.0519 0.9316 0.0994
-4.000 -0.3216 0.03042 0.02086 -0.0503 0.9279 0.1057
-3.750 -0.2984 0.02977 0.02025 -0.0499 0.9240 0.1142
-3.500 -0.2667 0.02905 0.01964 -0.0510 0.9200 0.1309
-3.250 -0.2264 0.02778 0.01899 -0.0539 0.9167 0.2098
-3.000 -0.2167 0.02560 0.01884 -0.0518 0.9134 0.5409
-2.750 -0.2306 0.02662 0.02077 -0.0401 0.9094 0.7723
-2.500 -0.2208 0.02789 0.02186 -0.0347 0.9047 0.8533
-2.250 -0.2142 0.02892 0.02279 -0.0278 0.9003 0.8956
-2.000 -0.1062 0.03053 0.02397 -0.0390 0.8966 0.9569
-1.750 0.1000 0.03078 0.02363 -0.0728 0.8964 0.9885
-1.500 0.1798 0.03063 0.02326 -0.0841 0.8933 1.0000
-1.250 0.2125 0.03077 0.02328 -0.0862 0.8887 1.0000
-1.000 0.2043 0.03142 0.02389 -0.0810 0.8806 1.0000
-0.750 0.2273 0.03173 0.02411 -0.0812 0.8750 1.0000
-0.500 0.2301 0.03231 0.02465 -0.0779 0.8674 1.0000
-0.250 0.2513 0.03267 0.02493 -0.0776 0.8608 1.0000
0.000 0.2535 0.03327 0.02549 -0.0741 0.8522 1.0000
0.250 0.2892 0.03355 0.02569 -0.0761 0.8460 1.0000
0.500 0.2888 0.03416 0.02627 -0.0720 0.8357 1.0000
0.750 0.3018 0.03467 0.02675 -0.0701 0.8266 1.0000
1.000 0.3378 0.03498 0.02701 -0.0720 0.8204 1.0000
1.250 0.3308 0.03565 0.02766 -0.0667 0.8096 1.0000
1.500 0.3322 0.03626 0.02825 -0.0629 0.8000 1.0000
1.750 0.3651 0.03660 0.02858 -0.0641 0.7942 1.0000
2.000 0.3559 0.03720 0.02917 -0.0586 0.7832 1.0000
2.250 0.3980 0.03752 0.02947 -0.0612 0.7791 1.0000
2.500 0.3792 0.03813 0.03008 -0.0542 0.7677 1.0000
2.750 0.4239 0.03842 0.03038 -0.0571 0.7640 1.0000
3.000 0.4066 0.03890 0.03086 -0.0504 0.7523 1.0000
3.250 0.4024 0.03940 0.03136 -0.0459 0.7424 1.0000
3.500 0.4359 0.03956 0.03154 -0.0469 0.7372 1.0000
3.750 0.4326 0.03994 0.03193 -0.0425 0.7264 1.0000
4.000 0.4741 0.03995 0.03200 -0.0444 0.7224 1.0000
4.250 0.4710 0.04049 0.03255 -0.0405 0.7113 1.0000
4.500 0.5116 0.04048 0.03260 -0.0422 0.7077 1.0000
4.750 0.5147 0.04117 0.03333 -0.0397 0.6967 1.0000
5.000 0.5288 0.04184 0.03406 -0.0387 0.6876 1.0000
5.250 0.5613 0.04198 0.03429 -0.0396 0.6824 1.0000
5.500 0.5755 0.04279 0.03517 -0.0388 0.6728 1.0000
5.750 0.6120 0.04270 0.03519 -0.0399 0.6681 1.0000
6.000 0.6248 0.04371 0.03629 -0.0392 0.6579 1.0000
6.250 0.6677 0.04307 0.03578 -0.0406 0.6536 1.0000
6.500 0.6851 0.04358 0.03640 -0.0399 0.6420 1.0000
6.750 0.7354 0.04209 0.03510 -0.0413 0.6385 1.0000
7.000 0.7505 0.04275 0.03588 -0.0404 0.6259 1.0000
7.250 0.8002 0.04066 0.03399 -0.0411 0.6206 1.0000
7.750 0.9054 0.03298 0.02676 -0.0401 0.6007 1.0000
8.000 0.9796 0.02623 0.02024 -0.0395 0.5826 1.0000
8.250 1.0186 0.02438 0.01855 -0.0389 0.5620 1.0000
8.500 1.0417 0.02363 0.01786 -0.0371 0.5303 1.0000
8.750 1.0533 0.02376 0.01796 -0.0346 0.4822 1.0000
9.000 1.0522 0.02483 0.01863 -0.0310 0.3960 1.0000
9.250 1.0326 0.02759 0.02046 -0.0264 0.2642 1.0000
9.500 1.0099 0.03121 0.02320 -0.0224 0.1758 1.0000
9.750 0.9995 0.03422 0.02573 -0.0194 0.1309 1.0000
10.000 0.9974 0.03664 0.02786 -0.0172 0.1110 1.0000
10.250 1.0030 0.03853 0.02969 -0.0157 0.0950 1.0000
10.500 1.0106 0.04033 0.03138 -0.0142 0.0833 1.0000
10.750 1.0226 0.04192 0.03295 -0.0129 0.0735 1.0000
11.000 1.0418 0.04340 0.03444 -0.0115 0.0644 1.0000
11.250 1.0683 0.04492 0.03587 -0.0107 0.0569 1.0000
11.500 1.0920 0.04644 0.03746 -0.0101 0.0518 1.0000
11.750 1.1467 0.04889 0.03990 -0.0110 0.0482 1.0000
12.000 1.1727 0.05156 0.04296 -0.0106 0.0471 1.0000
12.250 1.1911 0.05471 0.04649 -0.0097 0.0465 1.0000
12.500 1.2014 0.05815 0.05031 -0.0086 0.0464 1.0000
12.750 1.2046 0.06183 0.05435 -0.0071 0.0466 1.0000
13.000 1.2025 0.06564 0.05850 -0.0055 0.0469 1.0000
13.250 1.1949 0.06955 0.06271 -0.0040 0.0471 1.0000
13.500 1.1839 0.07361 0.06707 -0.0025 0.0473 1.0000
13.750 1.1701 0.07787 0.07159 -0.0013 0.0475 1.0000
14.000 1.1543 0.08239 0.07636 -0.0005 0.0478 1.0000
14.250 1.1372 0.08721 0.08140 -0.0001 0.0481 1.0000
14.500 1.1205 0.09240 0.08679 -0.0001 0.0484 1.0000
14.750 1.1071 0.09817 0.09271 -0.0006 0.0488 1.0000
15.000 1.0909 0.10289 0.09766 -0.0015 0.0493 1.0000
15.250 0.8466 0.09799 0.09339 0.0128 0.0513 1.0000
15.500 0.7720 0.10917 0.10489 0.0061 0.0534 1.0000
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